nasa stage 53 design report

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NASA Technical Pape, 1299

Aerodynamic Performanceof a 1.35-Pressure-RatioAxial-Flow Fan Stage

Walter M. Osborn, Royce D. Moore,and Ronald J. Steinke

OCTOBER 1978

NASA


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NASA Technical Paper 1299

Aerodynamic Performanceof a 1.35-Pressure-RatioAxial-Flow Fan Stage

Walter M. Osborn, Royce D. Moore,and Ronald J. SteinkeLewis Research CenterCleveland, Ohio

NASANational Aeronauticsand Space AdministrationScientific and TechnicalInformation Office1978


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CONTENTSPage

1

1DESIGN 2

S AND PROC ED URE 3Compressor Test Facility 3Test Stage 3Instrumentation 4Test Procedure 5Calculation Procedure 5

AN D DISCUSSION 6Overall Performance 6Radial Distributions 7Variations with Incidence Angle 7

O F RESULTS 8

A - SYMBOLS 10B - EQUATIONS 12C - DEFINITIONS AND UNITS USED IN TABLES 15

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A E R O D Y N A M I C P E R F O R M A N C E O F A 1 . 3 5 - P R E S S U R E - R A T I OA X I A L - F L O W F A N S T A G E

b y W a l t e r M . O s b o r n , R o y c e D . Moore , and R o n a l d J . S t e i n k eL e w i s R e s e a r c h C e n te r

SUMMARYT he overall and the blade-elemen t perform ances and the aerodynamic design pa-

are presented for a 1.35-pressure-ratio fan stage. This fan was designed forweight flow of 32 . 7 kilograms per second and a tip speed of 302. 8 meters per second.radial surveys of the flow conditions we re m ade over th e stable operating flow

at rotative speeds from 70 to 120 percent of design speed.At design speed th e stage peak efficiency of 0. 879 occurred at a pressure ratio of

32 9 and design flow. Stall margin was approximately 14 percent based on conditionsstall an d peak efficiency. At design speed and flow th e rotor efficiency was 0. 94 and

e pressure ratio was 1.360.

INTRODUCTIONT he Lewis research program on axial-flow fan s and compressors fo r advanced air-

is directed primarily toward reducing the size and weight of the fansd com pressors wh ile maintaining a high level of performance.

T o that end a series of fans has been designed and built to obtain de finitive inform a-for the selection of fans fo r propulsion systems fo r short-haul aircraft using the ex-

blown flap as the pow ered-lift system. T he externally blown flap needs a largeof low-velocity air for effective lift with low noise during takeoff an d landing (ref. 1) .

high air-bypass ratios, low pressure ratios, and low tip speeds should m eetcriterion. However, th e choice of fan pressure ratio and other parameters may de-on t radeoffs betw een fan aerodynamic perform ance and the low-noise goals. Per-

data must be obtained on suitable fans ov er a range of pre ssu re ratios andblown-flap short-haul aircraft .

he pressure ratios being investigated in this series w ere b etw een 1.15 and 1.40. Fansadjustable and fixed rotor blades are include d in the investigation.


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The experimental performances of three of the adjustable-rotor-blade fans in theseries are given in references 2 to 11 and of two of the fixed-rotor-blade fans in refer-ences 12 and 13. The design pressure ratios for these studies were from 1.15 to 1.25.All of the fans were tested at speeds as high as 120percent of design speed.

This report presents th e experimental performance of fan stage 53, another of thefixed-rotor-blade fans in the series. The 30-bladed, 50.8-centimeter-diameter fan wasdesigned for a tip-speed of 302.8 meters per second. The design pressure ratio of 1.35near the high end of the range for the series and occurs at a flow rate of 32.7 kilogramsper second. Overall performances of both the rotor and the stage, along with the blade-element performances of both rotor and stator, are presented. The data are presentedover the stable operating flow range of the stage at rotative speeds from 70 to 120 per-cent of design speed. Blade-element survey data were obtained at nine radial positions.T he data are presented in machine tabulated and plotted form. The symbols and equa-tions are defined in appendixes A and B. The abbreviations and units used in the tablesare defined in appendix C.

AE RO D YNAM IC DESIGNA compressor design computer program (refs. 14 to 16), which consists of a

streamline analysis subprogram, a blade-geometry subprogram, and a blade-coordinatesubprogram, was used in the design of fan stage 53.

T he streamline analysis subprogram (ref. 14)calculates the velocity vector dia-grams at several axial locations, including planes approximating the blade leading andtrailing edges. This program accounts for streamline curvatures and entropy gradi-ents. Weight flow, rotor speed, flow path geometry, boundary-layer blockages andradial distributions of rotor total pressure and stator outlet tangential velocity are inputsto this program.

T he results from the streamline analysis subprogram are then used in the blade-geometry subprogram (ref. 14). This program calculates the blade geometry that willsatisfy the vector diagrams.

After the blade geometry is defined for both the rotor and stator, the blade coor-dinate subprogram (ref. 16) is used to compute the blade elements on conical surfacesapproximating the stream surfaces passing through the blade. The program then stacksthese blade elements on a radial line about their centers of gravity and computes theCartesian blade coordinates for fabrication.

Because fan stage 53 was designed for low noise, the design procedure consisted ofan iteration of the aerodynamic, acoustic, and mechanical parameters. Thus, compro-mises were made to the aerodynamic parameters. The design procedure was similar tothat used for fan stage 51A (ref. 2 ).


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The overall design parameters for stage 53 are listed in table I, and the flow pathis shown in figure 1. The stage was designed for an overall pressure ratioo1. 35 at a w eight flow of 32. 7 kilograms per second (194.8 (kg/sec)/m of annulusT he design tip speed was 302.8 meters per second. Th e tip speed, rotor aero-

loading, and stator incidence angles were selected for low noise. T he totalat the rotor outlet decreases quadratically from tip to hub. T he rotor hub

decreases further locally where th e rotor relative fluid turning is limited to2. 7 for low noise. T he rotor and stator have double circular arc blade sections. Ro-r thickness to chord ratio varies cubically from 0. 03 at the tip to 0. 08 at th e hub.

variation reduces rotor vibration with no increase in rotor hub camber. Statorchord ratio is 0. 08 and is radially constant. There are 30 rotor blades and

8 stator blades. The rotor tip solidity is 1. 00, and the stator tip solidity is 1. 27.aspect ratio is 2 . 86 , and stator aspect ratio is 2. 62 based on the chord length at

blade height . For low noise the spacing between th e rotor trailing edge and theedge was made equal to four times the axial projection of the rotor blade

at the hub.The blade-element design parameters fo r rotor 53 and stator 53 are presented inn and III, and the rotor and stator blade geometries are presented in tables IV

APPARATUS AND PROCEDURECompressor Test Facility

The compressor stage was tested in the Lewis single-stage compressor test facil-y which is described in detail in reference 14 . Atmosphericair enters the test facil-y (fig. 2) through an inlet on the roof of the building and flows through th e flow meas-

into th e plenum chamber upstream of the test stage. Th e air thenthrough the experimental compressor stage into the collector from which it is

to the atmosphere.

Test StagePhotographs of the rotor and stator are shown in figures 3 and 4. Th e nonrotating

tip clearance of the rotor was a nominal 0. 050 centimeter at ambient conditions.he axial spacing between th e rotor-hub trailing edge and the stator-hub leading edgeas four times the rotor hub chord.


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Instrum entationThe compressor weight flow was determined from measurements on a calibratedthin-plate orifice. T he temperature at the orifice was measured with two Chromel-

constantan thermocouples. Pressures at the orifice were measured by calibrated trans-ducers.Radial surveys of the flow were made upstream of the rotor, between th e rotor andstator, and downstream of the stator (fig. 1). Photographs of the survey probes areshown in figure 5. Total pressure, total temperature, and flow angle were measuredwith a combination pro be (fig. 5(a)). T he thermocouple material for the combinationprobe is Chromel-constantan. T he static pressure was measured with an 8 C-shapedwedge probe (fig. 5(b)). E ach probe was positioned with a null-balancing, stream-direction-sensitive control system that automatically alined the probe to the direction offlow. T he probes were angularly alined in an air tunnel. T wo combination probes andtw o wedge static probes were used at each of the three measuring stations.Inner and outer wall static-pressure taps w ere located at the same axial stations asth e surve y probes. The circumferential locations of both types of survey probes alongwith inner- and outer-wall-static pressure-taps are shown in figure 6. T he combinationprobe downstream of the stator (station 3) was circumferentially traversed one statorblade passage (9. 5) counterclockwise from th e nominal value shown. An electronicspeed counter, in conjunction with a magnetic pickup, was used to measure rotativespeed (rpm). The estimated errors of the data based on inherent accuracies of the in-strumentation and recording system are as follows:Weight flow, kg/sec 0. 3Rotative speed, rpm 30Flow angle, deg 1Temperature, K 0.6oRotor-inlet total pressure, N/cm . . 0.01t\Rotor-outlet total pressure, N/cm 0.10nStator-outlet total pressure, N/cm 0.102Rotor-inlet static pressure, N/cm 0. 04

ORotor-outlet static pressure, N/cm 0. 07OStator-outlet static pressure, N/cm 0.07An indication of the consistency of the data can be observed by comparing th e integratedweight flow at each measuring station to the orifice weight flow.


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Test ProcedureThe stage survey data were taken over a range of weight flows from maximum flow

to th e near-stall at speeds of 70, 80, 90, 100, and 120 percent of design. D ata we rerecorded at nine radial positions fo r each speed and weight flow. At each radial posi-tion the two combination probes behind the stator were circumferentially traversed tonine different locations across the stator gap. T he two wedge probes wer e set at mid-gap because previous studies showed that the static pressure across th e stator gap wasconstant. Values of pressure, temperature, and flow angle were recorded at each cir-cum ferential position. At the last circumferential position values of pressure, temper-ature, and flow angle we re also recorded at stations 1 and 2. All probes w ere thentraversed to the next radial position, and the circumferential traverse procedure re-peated.

The weight flow at stall was obtained in the following m anner: during operation atthe near-stall condition, the downstream control valve was slowly closed in small de-crements. After each decrement the weight flow was obtained. The weight flow ob-tained jus t before stall occurred is called the stall weight flow.

Orifice weight flows, total pressures, static pressures, and temperatures were allcorrect ed to standard-day conditions based on the ro tor-inlet conditions.

Calculation ProcedureMeasured total temperatures and total pressures were corrected fo r Mach number

and streamline slope. T hese correct ions we re based on instrument probe calibrationsgiven in reference 17. The stream static pressure was corrected fo r Mach number an dstreamline slope based on an average calibration for the type of probe used.

Because of the size of the C-shaped, static-pressure wedges, it was not possible toobtain static-pressure measurements at 5, 10, and 95 percent of span. The static pres-sure at 95 percent span was obtained by assuming a linear variation in static pressurebetween the values at the inner wall and the probe measurement at 90 percent span. Asimilar variation was assumed between measurements at the outer wall and the 15 per-cent span to obtain the static press ure at 5 and 10 pe rcen t span.

At each radial position averaged values of the nine circumferent ial m easurementsof pressure, temperature, and flow angle do wnstream of the stator (station 3) were ob-tained. The nine total temp eratu res wer e mass averaged to obtain the stator-outlet totaltemperature. T he nine total pressures were energy averaged. T he mea sured values ofpressure, temperature, and flow angle we re used to calculate axial and tangential ve-locities at each circum ferential position. T he flow angles prese nted fo r each radial po-sition are calculated based on the se mas s-ave rage d axial and tangential velocities. T o

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obtain the overall performance, the radial values of total temperature were mass aver-aged, and the values of total pressure were energy averaged. At each measuring stationthe integrated weight flow was computed based on the radial survey data.

T he data, measured at the three measuring stations, were translated to the rotorand stator blade leading and trailing edges by the method presented in reference 14.Orifice weight flow, total pressures, static pressures, and temperatures were all cor-rected to sea-level conditions based on the rotor-inlet conditions.

RESULTS AND DISCUSSIONThe overall performances for the rotor and the stage are presented first. Radial

distributions of several performance parameters are then presented for both the rotorand the stator, followed by blade-element data. Finally, a brief discussion of the datais given.

.-All the plotted data, together with some additional performance parameters, arealso tabulated: The overall performance data are presented in table VI; and the blade-element data are given first for the rotor and then for the stator in tables VII and VIII.T he abbreviations and units.for the tabular data are defined in appendixC.

Overall PerformanceT he overall performance fo r rotor 53 is presented in figure 7 and for stage 53 in

f igure 8. -For both figures data are presented fo r speeds from 70 to 120 percent of de-sign speed. The design point values are shown by the solid symbols.

T he measured performance of rotor 53 at design flow (32.7 kg/sec) agrees closelywith the design values. The measured pressure ratio was 1. 360; the design value was1.-373. T he efficiency of 0. 940 is only 1 percentage point less than design. At designspeed the efficiency was essentially constant over a flow range from 32 . 7 to 34. 8 kilo-grams per second.

T he stage peak efficiency of 0. 879 occurred at design weight flow (32.7 kg/sec).T he measured pressure ratio was 1. 329; th e design value was 1. 351. T he differencebetween the measured rotor and stage efficiencies was 0.061; the design difference was0.050.

. Stall margin for this stage at design speed is approximately 14 percent, based onweight flow and pressure ratio at peak efficiency and stall conditions.


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Radial D istributionsThe radial distributions of several parameters for 100 percent of design speed are

in figure 9 for rotor 53 and in figure 10 for stator 53. In each figure dataweight flows: near choke, stage peak efficiency, and near stall.he design values are shown by the solid symbols. A line is fair ed throu gh the data at

efficiency condition. Temperature-rise efficiency, temperature ratio, pres-suct ion-s urfac e incidenc e angle, me ridional velocity ratio, deviation angle,parameter, total-loss coefficient, and diffusion factor are presented as func-

of percent span from th e blade tip.Rotor. - At the design weight flow of 32 . 7 kilograms per second, th e total-pressureis equal to design from the tip to 30 percent span and is slightly less than design30 percent span to the hub (fig. 9). ' The losses are higher th an design and t hus the

is lower at 5, 10, 90, and 95 pe rce nt span locations. Th e deviation anglesre essentially equal to design from the tip to midspan; however, they are significantlythan design from midspan to the hub. T he distribution of inlet meridional veloc-

y is different from design (see table vn(c)). T he velocity is high er than design in theegion and lower than design in. he hub region. T his together with th e radial distri-velocity ratio (fig. 9) indicate that th e flow has moved radially inward throu gh

e rotor at the design condition.Stator. - At the peak efficiency weight flow of 32 . 7 kilograms per second, th e meas-

angles were greater th an design values (fig. 10). T he ir radial distribu-also different from the design distribution. T he losses in the tip and hub re-are greater than design. T he diffusion factor is less than design over the entirespan. E xam ination of the circumferential distribution of total pressure indicated

e same lack of a well-defined wake in the stator hub region as that described in re fe r -18 . This type of wake pattern is indicative of flow separation on the blade surface

radial shift of flow through th e stators. Thus flow separation probably occurrede hub of stator 53; this is illustrated by the rapid rise in deviation angle and losses

Variations with Inciden ce AngleThe variations of selected blade-element parameters with suction-surface incidenceare presented for the rotor and the stator in figures 11 and 12. Th e data are pre-for 80, 100, and 120 percent of design speed for blade-element locations of 5, 10,

percent of span from th e blade tip. D esign values are shown byid symbols. In addition to the para m ete rs shown in the radial distribution plots, th e

relative Mach number is also presented in these figures.


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Rotor. - The rotor was designed for a suction-surface incidence angle of zero at allblade elements. At design speed the 5 percent blade element produced the desired pres-sure ratio and deviatio n angle at the design inciden ce angle; h ow ever, the energy addi-tion (temperature ratio) was slightly greater than design. T he losses were greater thandesign and thus th e efficiency was lower. At 10 percent span both pressure ratio andtemperature ratio we re higher than design. T he losses were greater than design andth e efficiency lower. At 30 percent span th e measured values were approximately equalto design. At 50, 70, 90, and 95 percent spans th e pressure ratios an d temperatureratios were slightly less than design. At 50 and 70 percent spans efficiency and losseswere approximately equal to design. At 90 and 95 percent spans th e deviation angles andlosses we re significantly great er than design.

The minimum measured loss occurred at suction -surface incidence angles less thanthe design values at all elements except 90 and 95 perc ent spans, w h ere losses changedvery little with changes in incidenc e angle. At 50 and 70 percent span, total-pressureratio showed essentially no variation with inciden ce angle.

Stator. - The stator was designed for a suction-surf ace incide nce angle, whichvaried from 2. 2 at the 5 percent element to -2. 5 at the 95 percent element. At allspan locations, the mea sure d deviation angles w ere significantly greater than designvalues. At the 30, 50, 70, and 90 perce nt span locations, minim um loss is about equalto or less than the design value and generally occurs at less than design inc idence angle.At 5, 10, and 95 percen t spans minimum losses are significantly greater than design.At the 5, 50, and 70 perce nt span locations th ere was little variation in losses with in-cidence angle. T he 95 perc ent span blade element has high losses at all incidenceangles, probably as a result of flow separation at the stator hub.

The data indicate that the 90 and 95 percent elements have a narrow incidence anglerange. At the low incidence angle th ese elements are probably choked. At the highincidence angle, they probably stall (indicated by the sharp rise in loss with increasingincidence angle). It is difficult to determine from th e data presented herein whether th eflow conditions in the stator hub region or those in the rotor tip region were the limitingfactor fo r minim um stable flow for the stage.

SUMMARY OF RESULTSThis report presents both the aerodynamic design parameters and the overall andblade-element performan ces of a 1.35-pressure-ratio fan stage. T he stage was de-

signed for a weight flow of 32 . 7 kilograms per second and a tip speed of 302. 8 metersper second. Detailed radial surveys of the flow conditions were made over th e stableoperating flow range at rotative speeds f rom 70 to 120 percent of design speed. Thefollowing principal results we re obtained from this investigation:8


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1. At design speed and design weight flow the rotor pressure ratio was 1. 360 andwas 0. 940. T he design-speed efficiency was essentially constant over a flow

of 32.7 to 34. 8 kilograms per second.2. The stage peak efficiency at design speed was 0. 879, and it occurred at design

flow. T he corresponding pressure ratio was 1. 329.3. Stall margin for this stage at design speed is approximately 14percent based onflow and pressure ratio at peak efficiency and stall conditions.

Research Center,National Aeronautics and Space Administration,

Cleveland, Ohio, May 18, 1978,505-04.


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A P P E N D I X A

SYMBOLS2

A annulus area at rotor leading edge, man 2Af frontal area at rotor leading edge, mC specific heat at constant pressure, 1004 J/kg/Kc aerodynamic chord, cmD diffusion factori mean incidence angle, angle between inlet air direction and line tangent to blade

mean camber line at leading edge, degi suction-surf ace incidence angle, angle between inlet air direction and line tangentss to blade suction surface at leading edge, degN rotative speed, rpm oP total pressure, N/cm 2p static pressure, N/cmr radius, cmSM stall marginT total temperature, KU wheel speed, m/secV air velocity, m/secW weight f low, kg/secZ axial distance referenced f rom rotor blade hub leading edge, cma cone angle, degCa slope of streamline, degO0 air angle, angle between air velocity and axial direction, deg/ 3 relative meridional air angle based on cone angle, arctan (tan / 3 * cos a /cos a ),\* HI C Sdegy ratio of specific heats (1.40) 26 ratio of rotor-inlet total pressure to standard pressure of 10.13 N/cm

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6 deviation angle, angle between exit air direction and tangent to blade meancamber line at trailing edge, deg

7 7 efficiency8 ratio of rotor-inlet total temperature to standard temperature of 288.2 KK angle between blade mean camber line and meridional plane, degK angle between blade suction-surf ace camber line at leading edge and meridionalss plane, dega solidity, ratio of chord to spacingu > total-loss coefficientw profile-loss coefficienta) shock-loss coefficientbSubscripts:ad adiabatic (temperature rise)id idealL E blade leading edgem meridional directionm om momentum-rise

polytropicref referenceTE blade trailing edget tipz axial direction0 tangential direction1 instrumentation plane upstream of rotor2 instrumentation plane between rotor and stator3 instrumentation plane downstream of statorSuperscript:' relative to blade

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A P P E N D I X B

EQUATIONS

Suction-surface incidence angle:'Kss (Bl )

Mean incidence angle:(B2)

Deviation angle:5 = (B3)

Diffusion factor:

fr VTE -


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2a(temperature rise) efficiency:

v(y-D/y

cos (B8)

TLEefficiency:

v(y-D/y

A

flow:

^ (BID6rotative speed:

j= (B12)*flow per unit annulus area;

6 (B13)an

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Mass flow per unit frontal area:w\/e

6Af

(B14)

Head-rise coeffic ient :

Flow coefficient:U tip

TE \ (y-D/yL - E ,

- 1 (B15)

lU tip/LE(B16)

Stall margin:

SM = "LE/stall \u /ref

x 100'Wef \ /sta11

(B17)

Polytropic effic iency:v ( y - D / y -

7? =' In L T E (B18)

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APPENDIX C

S

MARGIN

ANGLE

F

IC

O C

TC

COEFF

VEL R

DEFINITIONS AND UNITS USED IN TABLESabsoluteaerodynamic chord, cmmeridional air angle, degratio of actual flow area minus critical area to critical area

(where local Mach number is 1)angle between axial direction and conical surface representing

blade element, degdifference between mean camber blade angle and suction surface

blade angle at leading edge, degdeviation angle (defined by eq. (B3)), degdiffusion factor (defined by eq. (B4))adiabatic efficiency (defined by eq. (B9))inlet (leading edge of blade)incidence angle (suction surface defined by eq. (Bl) and mean

surface by eq. (B2))angle between blade mean camber line at leading edge and

meridional plane, degangle between blade mean camber line at trailing edge and

meridional plane, degangle between blade mean camber line at transition point and

meridional plane, degloss coefficient (total defined by eq. (B5)and profile by eq. (B6))loss parameter (total defined by eq. (B7)and profile by eq. (B8))meridionalmeridional velocity ratiooutlet (trailing edge of blade)percent of blade span from tip at rotor outletsuction-surface camber ahead of assumed shock location, deg

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PRESSPROFRADIIRELRIRORPRPMSETTING A N G L ESOLIDITYSPEEDSSSTREAMLINE

SLOPETANGTEMPTITMTOTOTTOTAL C A M B E RT U R N RATE

VELW T FLOWZIZMCZOZTC

opressure, N/cmprofileradius, cmrelative to bladeinlet radius (leading edge of blade), cmoutlet radius (trailing edge of blade), cmradial positionequivalent rotative speed, rpmangle between aerodynamic chord and meridional plane, degratio of aerodynamic chord to blade spacingspeed, m/secsuction surfaceslope of streamline, deg

tangentialtemperature, Kthickness of blade at leading edge, cmthickness of blade at maximum thickness, cmthickness of blade at trailing edge, cmtotaldifference between inlet and outlet blade mean camber lines, degratio of change in blade angle per unit path distance for front

blade segment to the change in blade angle per unit path distancefor af t blade segment

velocity, m/secequivalent weight flow, kg/secaxial distance from inlet hub to blade leading edge, cmaxial distance from inlet hub to blade maximum thickness point, cmaxial distance from inlet hub to blade trailing edge, cmaxial distance from inlet hub to transition point, cm

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R E F E R E N C E S1. Rosen, George: An Engine for Quiet STOL Propulsion. Astronaut. Aeronaut.,

vol. 9, no. 12, Dec. 1971, pp. 50-55.2 . Osborn, Walter M.; and Steinke, Ronald J.: Performance of a 1.15 Pressure RatioAxial-Flow Fan Stage With a Blade Tip Solidity of 0. 5. NASA TM X-3052, 1974.3. Kovich, George; and Steinke, Ronald J.: Performance of a Low-Pressure-Ratio,

Low-Tip-Speed Fan Stage With Blade Tip Solidity of 0. 65. NASA TM X-3341, 1976.4. Kovich, George; Tysl, Edward R.; and Moore, Royce D.: Performance of a Low-

Pressure-Ratio Fan Stage at Two Off-Design Blade Setting Angles. NASA TMX-3447, 1977.

5. Kovich, George; and Moore, Royce D.: Performance of 1. 15-Pressure-Ratio FanStage at Several Rotor Blade Setting Angles with Reverse Flow. NASA TM X-3451,1976.

6. Lewis, George W., Jr.; Moore, Royce D.; and Kovich, George: Performance ofa 1. 20-Pressure-Ratio STOL Fan Stage at Three Rotor Blade Setting Angles. NASAT M X - 2 8 3 7 , 1973.

7. Lewis, George W., Jr.; and Tysl, Edward R.: Overall and Blade-Element Perform-ance of a 1. 20-Pressure-Ratio Fan Stage at Design Blade Setting Angle. NASA TM

X-3101, 1974.8. Lewis, George W., Jr.; Osborn, Walter M.; and Moore, Royce D.: Overall and

Blade-Element Performance of a 1.20-Pressure-Ratio Fan Stage with Rotor BladesReset Minus 5. NASA TMX-3338, 1976.

9. Lewis, George W., Jr.; and Kovich, George: Overall and Blade-Element Perform-ance of a 1. 20-Pressure-Ratio Fan Stage with Rotor Blades Reset Minus 7.NASA TMX-3342, 1976. '

Moore, Royce D.; Lewis, George W., Jr.; and Tysl, Edward R.: Performance ofa Low-Pressure Fan Stage with Reverse Flow. NASA TM X-3349, 1976.

Moore, Royce D.; and Kovich, George: Aerodynamic Performance of Two Variable-Pitch Fan Stages. NASA TM X-73416, 1976.

2 . Moore, Royce D.; and Steinke, Ronald J.: Aerodynamic Performance of a 1. 25-Pressure-Ratio Axial-Flow Fan Stage. NASA TM X-3083, 1974.

Lewis, George W., Jr.; and Moore, Royce D.: Aerodynamic Performance of a1. 20-Pressure-Ratio Fan Stage Designed for Low Noise. NASA TMX-3430,1976.

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14. Urasek, Donald C.; and Janetzke, David C.: Performance of Tandem-Bladed Tran-sonic Compressor Rotor with Tip Speed of 1375 Feet Per Second. NASA TMX- 248 4 , 1972.

15. Ball, Calvin L.; Janetzke, David C.; and Reid, Lonnie: Performance of 1380-Foot -Per-Second-Tip-Speed Axial-Flow Compressor Rotor with Blade Tip Solidity of1. 5. NASA TM X-2379, 1972.

16. Grouse, James E.; Janetzke, David C.; and Schwirian, Richard E.: A ComputerProgram for Composing Compressor Blading from Simulated Circular-Arc Ele-ments on Conical Surfaces. NASA T N D-5437, 1969.

17. Glawe, George E.; Krause, Lloyd N.; and Dudzinski, Thomas J.: A Small Com-bination Sensing Probe for Measurement of Temperature, Pressure, and FlowDirection. NASA TN D-4816, 1968.

18. Lewis, George W.; Urasek, Donald C.; and Reid, Lonnie: Effec ts of Reset Statorsand a Rotating, Grooved Hub on Performance of a 1. 92-Pressure Ratio Compres-sor Stage. NASA TM X-3472 , 1977.

TABLE I. - DESIGN OVERALLPARAMETERS FOR

STAGE 53-53

ROTOR TOTAL PRESSURE RATI O 1.373STAGE TOTAL PRESSURE RATIO 1.351ROTOR TOTAL T EMPERATURE RATIO 1.100STAGE TOTAL TE MPERAT URE RATIO 1.100ROTOR ADIABATIC EFFICIENT 952STAGE ADIABATIC E F F I C I E N C Y 902ROTOR POLYTROPIC E F F I C I E N C Y 95 4STAGE P O L Y T R O P I C E F F I C I E N C Y 90 6ROTOR HEAD RISE COE F F I C IE N T 29 9STAGE HEAD RISE COE F F I C IE N T 28 4F L O W COE F F I C IE N T 633H T FLOW P ER U N I T F R O N T A L AREA 163.247M T F L O W P E R U N I T A N N U L U S A R E A 194.829HT FLOW 32.659R P M 1 1 4 5 9 . 2 0 0T I P S P E E D 3 0 2 . 8 2 0

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TABLE H. - D E S I G N BLADE-ELEMENT PARAMETERSFOR ROTOR 53

R A D I IRPTIP123456789HUB

RPTIP123456789HUB

I N25.23524.42223.56822.73720.28517.17014.23112.14411.47310.81410.160AB S

I N164.41 74.51 8 1 . 5184.5192.61 98.12 0 0 . 1200.5200.6200.6200.6

OUT24.49823.78123.06422.34820.19717.32914.4611 2 . 3 1 111.59410.87710.160V E LOU T219.32 1 6 . 02 1 4 . 82 1 5 . 821 6.72 1 8 . 02 1 9 . 8222.4223.5224.8226.1

A B S H A C K N OR PTIP123456789HUB

I N.495.527.549.559.585.603.609.611.611.611.611

OU T.635.625.622.625.629.635.644.656.661.666.672

ABSI N.0.0.0.0.0.0.0.0.0.0.0REL

I N344.5341 .1336.0329.4310.4285.8263.1247.9243.3238.9234.7

B E T A NOUT30.531 .832.833.435.739.041 .743.443.743.944.1V E LOU T262.82 5 1 . 1241 .4234.02 1 0 . 9183.6166.31 6 1 . 6162.2163.9166.3

R EL H A C K N OI N1.0371.0301.017.998.943.870.801.755.741.728.715

P E R C E N T I N C I D E N C ERPTIP123456789HUB

S P A N.005.001 0.0015.0030.0050.0070.0085.0090.0095.00100.00

H E A N3.63.63,83.94.75.86.87.17.27.17.1

SS-.-.-.-......0-.1

OUT.761.726.698.678.612.535.488.476.480.486.494

D E V4.14.44.74.95.55.95.95.85.85.75.8

DE LI N61.559.257.355.951.646.140.536.034.532.931.3M E R I DI N1 64.4174.51 81 .5184.5192.61 9 8 . 1200.1200.5200.6200.6200.6

B E T A HO U T44.043.141.639.733.422.79.5-1 .8-5.5-8.9-1 2.3V E LOUT188.91 83.51 80.51 80.21 7 6 . 1169.41 64.01 6 1 . 51 6 1 . 51 62.0162.5

M E R I D H A C K N OI N.495.527.54?.559.585.603.609.61 1.61 1.61 1.611

D - F A C T.398.425.444.454.488.527.532.503.483.459.430

OUT.547.531.522.522.511.494.481.476.477.480.483E F F.932.937.943.949.961.960.957.937.928.918.907

T O T A L T E M PI N288.2288.2288.2288.2288.2288.2288.2288.2288.2288.2288.2

R A T I O1 . 1 1 3.112. 1 1 1. 1 1 0.106.099.088.078.074.070.066T A N G V E L

I N.0.0.0.0.0.0.0.0.0.0.0

OUT1 1 1 . 3113.91 1 6 . 51 1 8 . 81 26.31 37.2146.2152.9154.5155.9157.2S T R E A M L I N E SLOPEI N-9.35- 8 . 1 1-6.87

-5.74-3.04-.82.20.40.38.32.26LOSSTOT.047.044.041.037.030.032.036.051.057.063.070

O U T-10.88-8.97-7.35-6.07-3.02-.63.41.54.48.36.24C O E F FP R O F-.006.002.007.009.022.032.036

.051.057.063.070

T O T A LI N1 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 4W H E E L

I N302.82 9 3 . 1282.8272.8243.4206.01 7 0 . 81 4 5 . 71 37.7129.81 2 1 . 9M E R I DV E L R1 . 1 4 91 . 0 5 1.995.977.914.855.820.805.805.807.810LOSST O T.01 7.016.014.013.010. 0 1 1. 0 1 0.013.013.014.014

P R E S SR A T I O.419.419.418.415.403.372.325.280.263.245.227S P E E DOU T294.0285.4276.8268.2242.4208.01 7 3 . 5147.71 39.11 30.51 2 1 . 9

P E A K SSH A C K N Q.626.567.527.506.3671 . 1 8 81 . 0 1 5.893.852.810.763

P A R A HPROF- . 0 0 2.001.003.003.007. 0 1 1.01 0.013.013.014.014

19


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T A B L E in. - D ESI G N BLA D E - E L E M E N T P A R A M E T E R SFO R STA TO R 53

R A D I IR PT I P123456789H U B

I N24. 16823.39522.71822.04420.01417.31614.59912.51011.78&11.04810.160

O U T24.16823.42222.77222.12620.19717.67215.17613.26312.60411.9351 1 . 1 5 3A B S V E L

RPT I P12345789H U B

I N226.6228.1229.2230.12 3 1. 1229.5224.9219.8216.42 12 . 1207.2

O U T194.7194.8194.6194.1190.9182.416 8 . 1152.4148.0143.8139.0A B S M A C H N OR PT I P12

3456789H U B

I N.658.663.667.670.675.672.661.648.638.626.611

O U T.559.559.559.558.549.525.485.440.427.415.402

A B SI N29.930.53 1 . 131.633.536.84 0 . 143.244.746.448.5R E L

I N226.6228.1229.2230.12 3 1 . 1229.5224.9219.8216.42 12 . 1207.2

B E T A MO U T.0.0.0.0.0.0.0.0.0.0.0V E LOUT19 4 . 7194.8194.619 4 . 119 0 . 918 2 . 41 6 8 . 1152.4148.0143.81 3 9 . 0

R E L H A C K N OI N.658.663.667.670.675.672.661.648.638.626.611

P E R C E N T I N C I D E N C ER PT I P123456189H U B

S P A N.005.001 0 . 0 015 . 0 030.0050.0070.0085.0090.0095.00106.00

M E A N9.99.9.8.7.6.5.5.4.4.4.

5179991852

SS2.62.21.81.5.7-.2- 1 . 2-2.0-2.2-2.5-2.7

O U T.559.559.559.558.549.525.485.440.427.415,.402D E V5.05.25.45.55.96.36.76.97.07.17.3

R E L B E T A HI N29.930.53 1 . 13 1. 633.536.84 0 . 143.244.746.448.5H E R I DI N196.419 6 . 5196.4196.0192.8183.917 2 . 01 6 0 . 2153.9146.313 7 . 2

O U T.0.0.0.0.0.0.0.0.0.0.0V E LO U T19 4 . 719 4 . 8194.61 9 4 . 1190.918 2 . 41 6 8 . 1152.414 8 . 0143.813 9 . 0

H E R I D H A C K N OI N.570.571.571.571.563.538.505.472.454.432.405

D - F A C T.337.340.342.345.354.374.405.445.450.451.451

O U T.559.559.559.558.549.525.485.440.427.415.402E F F.000.000.000.000.000.000.000.000.000.000.000

T O T A L T E M PI N320.8320.5320.33 1 9 . 9318.7316.6313.43 1 0 . 7309.6308.43 0 7 . 1

R A T I O1 . 0 0 01 . 0 0 01 . 0 0 01 . 0 0 01 . 0 0 01 . 0 0 01 . 0 0 01 . 0 0 01 . 0 0 01 . 0 0 01 . 0 0 0T A N G V E L

I N1 1 2 . 9115 . 81 1 8 . 2120.5127.513 7 . 4144.915 0 . 5152.115 3 . 51 5 5 . 2

O U T.0.0.0.0.0.0.0.0.0.0.0S T R E A M L I N E S L O P EI N- . 0 2.29.57

.861. 8 23.304.905.855.C75.735.57L O S ST O T.056.053.051.051.050.060.075.098.108.122.136

O U T- . 0 1.25.50.751.623.064.926.597.097.588 . 15

C O E F FP R O F.056.053.051.051.050.060.075.098.108.122.136

T O T A LI N14 . 3 914.3814 . 3 714.3514.2213.9013.4312 . 9 712 . 8 012.6212.39W H E E LI N.0.0.0.0.0.0.0.0.0.0.0

H E R I DV E L R.991.991.991.990.990.992.977.952.962.9831 . 0 1 3L O S ST O T.022.020.019.018. 0 16. 0 17.018.020.021.022.023

P R E S SR A T I O.986.986.987.987.987.984.981.976.974.972.970S P E E DO U T.0.0.0.0.0.0.0.0.0.0.0

P E A K S SM A C H N O.862.858.853.847.837.817.770.726.706.685.663

P A R A MP R O F.022.020.019.018.016. 0 17.018.020.021.022.023

20


24/109

TABLE IV. - BLADE GEOMETRY FOR ROTOR 53

P E R C E N T R A D I IR PT I Pt23456789H U B

R PTIP1234S6789HUB

S P A N0.5.10.15.30.50.70.85.90.95.1 0 0 .B L A D ET I.041.041.041.042.051.065.073.083.084.083.082

A E R OR PT I P123456789HUB

C H O R D55555555555

.163.165.154.145.133.134.135.136.135.134.142

R I25.23524.42223.56822.73720.28517.17014.23112.14411.47310.81410.160

R O24.49823.78123.06422.34820.19717.32914.46112.31111.59410.87710.160

T H I C K N E S S E ST M.207.-209.21 4.222.258.319.375.406.410.41 1.412S E T T I N GA N G L E48.6746.944 5 . 1 343.3337.4828.511 8.631 0 . 6 38.085.573.07

T O.041.041.041.041.052.063.074.083.084.083.082T O T A L

C A M B E R1 7 . 8 71 6 . 9 116.641 7 . 2 81 9 . 0 723.583 0 . 1 736.5538.5140.4042.30

i B L A D E A N G L E SK I C57.6755.4353.4852.0047.0240.3033.6728.8627.3025.7524.22

K T C48.6846.9845.1643.3637.4828.511 8.581 0 . 5 98 . 0 55.553 . 0 8

K O C39.7938.5236.8534.7227.9516.723.50-7.69- 1 1 . 2 1-14.65-18.08

D E L T AINC3.673.703.793.934.605.706.647.047.097 . 1 27 . 1 4

C O N EA N G L E-12.422-10.420-7.939-5.957-1.2422.0142 . 7 1 21 . 8 9 11 .364. 7 1 0.057

A X I A L D I M E N S I O N SZ I.899.828.762.705.537.327.155.061.038.01 9.000

S O L I D I T Y.9911 . 0 2 31 . 0 5 51 . 0 9 01 . 2 1 11 . 4 2 11 . 7 0 92.0052 . 1 2 62.2602.41 6

ZMC2.4262.4332.4382.4402.4492.4602.4802.5092 . 5 1 92.5302.540T U R N I N GR A T I O1 .0001 .0001 .000.000.000.000.000.000.000.000.000

ZTC2.4262.4332.4382.4402.4492.4602.4802.5092.51 92.5302.540

P H I S S15.401 3 . 7 512.641 2 . 2 110.36.7.905 . 1 23 . 0 32.301 .56.83

44444455555

Z O.243.310.375.439.620.843.020. 1 0 7.122.129.1 35C H O I C EM A R G I N.156.125. 1 1 0. 1 1 3. 1 0 7.1 05. 1 0 0.088.077.063.049

21


25/109

TABLE V. - BLADE GEOMETRY FOR STATOR 53

RPTIP123456789HU BR PTIP123456789HUB

R PTIP123456789H U B

P E R C E N TS P A N0.5.10.15.30.50.70.85.90.95.1 0 0 .B L A D ET I.081.081.081.081.0.81.081.082.082.082.082.082

A E R OC H O R D5.0655.0645.0655.0675.0705.0775.0975 . 1 1 65.1255.1365.159

R A D I IR I24.16823.39522.71822.04420.01417.31614.59912.51011.78511.04810.160

R O24.16823.42222.77222.12620.19717.67215.17613.26312.60411.93511.153

THICKN E SSEST M.405.405.405.405.406.406.408.409.410.411.412S E T T I N GA N G L E7.457.908.298.689.861 1 . 7 913.8815.7616.5917.5318.69

T O.081.081.081.081.081.081.082.082.082.082.082T O T A LC A M B E R24.9926.2627.3328.353 1 . 4 036.1240.8444.8346.6348.665 1 . 1 2

B L A D E A N G L E SK I C19 . 9 52 1. 0 321.9522.8525.5429.793 4 . 1 737.9539.644 1. 5 543.84

K T C7.467.908.298.679.841 1 . 7 313.7615.5616.3517 . 2 518.32

K O C- 5 . 0 4-5.23- 5 . 3 7- 5 . 5 1-5.86-6.33-6.67-6.87-6.98- 7 . 1 2-7.27

DELTAI N C7.307.297.287.277.237 . 1 77 . 1 07.047.026.996.96

C O N EA N G L E.057.310.612.9352.0924 . 1 0 86.6948.7969.58910.4281 1 . 7 1 5A X I A L D I M E N S I O N SZI25.45925.46625.47125.47725.49225.52225.56225.60025.62025.64325.671

S O L I D I T Y.1.2671. 3 0 81. 3 4 71.3881.5251. 7 5 52 . 0 7 12 . 4 0 12.5422.7032.928

Z M C27.93527.93527.93527.93527.93027.92127.91327.90127.896i - . 8 9 22/.B86T U R N I N GR A T I O.000.000.000.000.000.000.000.000.000

.000.000

ZTC27.93527.93527.93527.93527.93027.92127.91327.90127.89627.89227.886

P H I S S3 . 8 13 . 8 13.803.763.874.193.993.723.713.743.78

Z O30.48230.48330.48430.48630.48530.48130.47930.46930.46630.46330.460C H O K EM A R G I N. 13 1.128.126.123. 119.126.137.145.155.168.183

2 2


26/109

T A B L E VI. - O V E R A L L P E R F O R M A N C E FORSTAGE 53(a) 70 Percent of design speed

R E A D I N G N U X 3 E RR O T O R T O T i L P R E S S U R E R A T I O .S T A G E T O T A L P R E S S U R E R A T I O . .R O T O R T O T A L T E M P E R A T U R E R A T I OS T A G E T O T A L T E M P E R A T U R E R A T I OR O T O R T E X ? . R I S E E F F I C I E N C Y .S T A GE T E M P / R I S E E F F I C I E N C Y .R O T O R M O M E N T U M R I S E E F F I C I E N C YR O T O R H E AD R I S E C O E F F I C I E N T .S T A GE H EA D R I S E C O E F F I C I E N T .F L O W C O E F F I C I E N T -X T F L O W P E R U N I T F R O N T A L A R E A ,X T F L O W P E R U N I T A N N UL U S A R E AX T F L O W AT O R I F I C E , .W T F L O W A T R O T O R I N L E TX T FLOX A T R O T O R O U T L E TW T FLOX AT S T A T O R OUTLET . . . .R O T A T I V E S P E E D - .P E R C E N T O F D E S I G N S P E E D

302"I . I 1 C1 .0771 . 0 3 01.0331 . 0 1 0

0.6560.9450 . 1 9 50 .15 70.798151.74

1 8 1 . 1 030.:3630.3330.3231.018024.7

70.0

30231 . 1 3 0i . i i 41.0351.0551.0260.8950 . 9 E O0.2310 . 2 C 40 . 7 1 9139.7!-166.742 7 .9 527.9227:9327.987986.3 69 . 7

30291 . 1 4 51 . 1 3 11.0381.0391 . 0 1 70 .9200.9860 .2540.2350 .645127.93152.6325 .5925.5425 .7225.717985.169 .7

30501 . 1 5 71 . 1 4 51 . 0 4 31 . 0 4 40 .9770.8990 .9670.2750 .2550.565114 . 67136.862 2 . 9 422 . 8 825 .2223.298009 .569.9

3 0 3 11.1571 . 1 4 31 . 0 4 81 . 0 4 30.8820 .3060.87!0 .2750 . 2 5 10 .47698.42117 .4519.6919.632 0 . 0 820.518009.369. 9-

(b) 80 Percent of design speedR E A D I N G N U M B E RR O T C R T O T A L P R E S S U R E R A T I OS T A G E T O T A L P R E S S U R E R A T I OR O T O R T O T A L T E M P E R A T U R E R A T I O .....S T A G E T O T A L T E M P E R A T U R E R A T I OR O T O R T E X ? . R I S E E F F I C I E N C Y . . . . . .S T A G E T E H ? . R I S E E F F I C I E N C Y . - . . .R O T O R M O M E N T U M R I S E E F F I C I E M C YR O T O R H E A D R I S E C O E F F I C I E N TS T A G E . H E A D R I S E C O E F F I C I E N TF L O W C O E F F I C I E N TW T F L O W P E R U N I T F R O N T A L A R E AX T F L O W P E R U N I T A N N U L U S A R E AW T F L O X A T O R I F I C EK T F L O X A T R O T C R I N L E TX T F L O X A T R O T O R O U T L E TW T F L O W A T S T A T O R O U T L E TR O T A T I V E S P E E P 9 1 8 0 . 9P E R C E N T OF D E S I G N S P E E D . ...:....

3 0 1 !1 . 1 7 11 . 1 3 71 . 0 4 61 . 0 4 70 . 9 3 10 . 7 9 40 . 5 5 50 . 2 2 70 . 1 6 40 . 7 4 91 5 9 . 8 9 -

1 9 0 . 8 33!;993 1 . 9 43 2 . 0 65 2 . 7 39 1 8 0 . 98 0 . 1

3 0 1 21 . 1 3 31 . 1 6 91 . 0 5 01 . 0 5 11 . 0 0 20 . 3 9 70 . 9 7 20 . 2 4 70.2230 . 6 8 915 0 -.63

179.773 3 . 1 33 0 . 1 13 0 . 2 730 ".4 59197.. - I8 0 . 3

3 0 1 41 . 2 0 1. 1 . 1 8 6. 1.0541. 0 5 50 . 9 9 10 . 9 1 60 . 9 7 00 . 2 6 40 . 2 4 60 . 6 3 21 4 0 . 9 5168.232 8 . 2 02 8 . 1 72 8 . 3 62 8 . 6 89 188 .-380 . 2

3 0 151 . 2 1 11 . 1 9 61. 0 5 81 . 0 5 90 . 9 6 60 . 8 9 60 . 9 5 7. 0 . 2 7 50 . 2 5 70 . 5 8 11 3 2 . 0 01 5 7 . 5 42 6 . 4 126.5526.5626.93920 P.O8 0 . 3

3 0 0 71.2121 . 1 9 61 . 0 6 11 . 0 6 10 . 5 2 90 . 8 S 70 . 9 2 40 . 2 7 80 . 2 5 90 . 5 3 7

1 2 3 . 1 2U6.952 4 . 6 32 4 . 6 22 5 . 0 125.399 1 7 3 . 58 0 . 1

3 0 0 61 . 2 0 71 . i 891 . 0 6 41 . 0 6 30 . 8 6 60 . 6 0 50 . 8 5 70 . 2 7 20 . 2 5 00 . 4 E 91 1 3 . 5 4

1 3 5 . 5 022.7':2 2 . 6 82 3 . 0 52 3 . 6 99 1 5 6 . 58 0 . 0

(c) 90 Percent of design speedR E A D I N G N U M B E RR O T O R T O T A L P R E S S UR E R A T I OS T A G E T O T A L P R E S SU R E R A T I OR O T O R T O T A L T E M P E R A T U R E R A T I O . . . .S T A G E T O T A L T E M P E R A T U R E R A T I O . . . .R O T O R . T EM P. R I S E E F F I C I E N C YS T A GE T E MP . R I S E E F F I C I E N C Y . . . . .R O T O R M O M E N T U M R I S E E F F I C I E N C Y . . . .R O T O R H E A D R I S E C O E F F I C I E N TS T A GE H E A D R I S E C O E F F I C I E N TF L O W C O E F F I C I E N TW T F L O W PER U N I T F R O N T A L A R E A . . . .X* F L O W PER U N I T A N N U L U S A R E A . . . .X T F L O X A T O R I F I C EX T F L O X A T R O T O R I N L E TX T F L O X A T R O T O R O U T L E TX T F L O X A T S T A T O R O U T L E TR O T A T I V E SPEEDP E R C E N T O F D E S I 6 N S PE E D

. . 3016.1 .242 1.2091 . 0 5 51 .0650.985-0.8S20.955. . 0.2450 . 2 1 8 . - .715 167.662 0 0 . 1 233.5535.4853.7254.24 1 0 3 1 1 . 1 . . 90.0

29971 , 2 6 11 .2591 . 0 7 01 . 0 7 00.977-0.9050.5530.257 0.2450.655159.66190.553 1 . 9 43 i . 6 9 -3 2 . 1 332.591 0 3 1 2 . 490.0

29981 .'2751 .254 '1 . 0 7 41 . 0 7 30.9700 / 5 1 0 -0.961 .0.279"0.259V0.6261 5 5 . 1 5182.7530.65. 50.5750.843 1 . 3 6. 1 0 3 3 1 . 590.2

29991 . 2 3 V- . 1.2591 .0761 . C 7 6'0.558-0,89.10.9420.2340.2640.5S5145.53173.692 9 . 1 !29.0729.2929.8710336.090.2

30001 .2751.2551 . 0 7 91 . 0 7 80 . 9 1 7

- 0 - . 85 80.9070.2800.2600.545137.77164.4227.5627.4827.7528.441 0 3 3 1 . 190.2

3 0 0 11 . 2 S 71.2441 . 0 8 2I . C S OO.S570.8040..8490.2720.2-00.505128.93153.6725.7925.802 6 . 1 72 7 . 0 11 0 3 3 4 . 190.2

23


27/109

TABLE VI. - Concluded,(d) 100 Percent of design speed

R E A D I N G N U M B E R 301)7 2996 2593 2994 2935 3028R O T O R T O T A L P R E S SU R E R A T I O 1.514 1.335 1.360 I.356 1.356 1.554S T A G E T O T A L PRESSURE R A T I O 1.275 1.303 -329 1.334 1.522 1.517R O T O R T O T A L T E M P E R A T U R E R A T I O LOSS 1.092 '.098 i . i O t 1.102 1.104S T A GE T O T A L T E M P E R A T U R E R A T I O LOSS 1.091 '-056 1.099 LOSS 1.10!R O T O R T EM P . R I S E E F F I C I E N C Y 0.941 0.945 0.940 0.925 0.850 0.872S T AG E T E MP . R I S E E F F I C I E N C Y 0.845 0.873 0.879 0.870 0.8'iS 0.808R O T O R M O M E N T U M R I S E E F F I C I E N C Y 0.913 0.926 0.929 0.921 0.883 0.859R O T OR H E A D R I S E C O E F F I C I E N T 0.25S 0.274 0.289 0.254 0.26S 0.2S5S T A GE H E A D R I S E C O E F F I C I E N T 0.227 0.252' .0.267 0.271 0.262 0.258F LO W C O E F F I C I E N T 0.6S5 0.661 0.620 0.584 0.548 0.519W T F L O W P E R U N I T F R ON T A L A R E A 1 7 3 . 9 8 1 7 0 . 5 7 1 6 3 . 5 0 156.85 149.37 143.57W T F L O W P E R U N I T A N N U L U S A R E A 207.65 203.57 1 9 5 . 1 4 1 87.20 1 7 8 . 2 6 1 7 1 . 3 5W T F L O W A T O R I F I C E 34.81 34.12 52.71 31.58 29.63 28.72W T F L O W A T R O T O R I N L E T 34.73 34.09 32.67 31.56 29.55 28.74W T F L O W A T R O T O R O U T L E T 35.10 34.36 32.93 31.74 30.34 29.3!W T F L O W A T S T A T O R O U T L E T 35.57 35.04 33.73 .32.50 51.20 30.29R O T A T I V E SPEED I U 6 5 . - 1 1 1 46 8 . 0 1 1 4 6 6 . 9 1 1 4 6 7 . 0 1 1 4 6 9 . 0 1 1 4 7 0 . 3P E R C E N T O F D E S I G N S PE E D 100.0 '00.1 100.1 100.1 100.1 100.1

(e) 110 Percent of design speedR E A D I N G N U M B E R 3023 3024R O T O R T O T A L P R E S SU R E R A T I O ........ 1.455 1.450S T A G E T O T A L P R E S S UR E R A T I O 1.410 1.401R O T O R T O T A L T E M P E R A T U R E R A T I O 1.125 1.128S T A G E T O T A L T E M P E R A T U R E R A T I O 1.121 1.124R O TO R T EM P . R I S E E F F I C I E N C Y 0.908 0.375S T A G E TEMP. RISE E F F I C I E N C Y 0.855 0.813R O T O R M O M E N TU M R I S E E F F I C I E N C Y 0.854 0.8S3R O T OR H E A D R I S E C O E F F I C I E N T Q 2 9 5 0.294S T A G E H E A D R I S E C O E F F I C I E N T 0 270 0.26'GF L O W C O E F F I C I E N T 0.592 0.559W T F L O W P E R U N I T F R O N T A L A R E A 168.48 1 5 7 7 5W T F L O W P E R U N I T A N N UL U S A R E A ...... 2 0 1 0 8 1 8 8 2 8W T F L O W A T O R I F I C E 33.71 3 1 ! 5 6W T F L O W A T R O T O R I N L E T 33.57 3 1 5 9W T F L O W AT R O T O R O U T L E T , 34.24 32 26W T F L O W A T S T A T O R O U T L E T 35.41 3 5 8 2R O T A T I V E S P E E D 12578.0 12555.0P E R C E N T OF D E S I G N S P E E D . . . 109.8 109.6

(f) 120 Percent of design speedR E A D I N G N U M B E RR O T O R T O T A L PRESSURE R A T I OS T A G E T O T A L P R E S S U RE R A T I OR O T O R T O T A L T E M P E R A T U R E R A T I O ....S T A G E TO T A L T E M P ER A T U R E R A T I O ....R O T O R TE M P. R I S E E F F I C I E N C YS T A G E T E M P . R I S E E F F I C I E N C YR O T O R M O M E N T U M R I S E E F F I C I E N C Y . . . .R O T O R H E A D R I S E C O E F F I C I E N TS T A G E H E A D R I S E C O E F FI C I E N T . .F L O W C O E F F I C I E N TW T F L O W PER U N I T F R O N T A L A R E A . . . .W T F L O W P E R U N I T A N N U L U S A R E A . . . .W T F L O W A T O R I F I C EW T F L O W A T R O T O R I N L E T . . . : . . . .W T F L O W A T R O T O R O U T L E TW T F L O W A T S T A T O R O U T L E TR O T A T I V E SPEEDP E R C E N T O F D E S I G N S PE E D

. . 30331 .4391 .3851 . 1 3 01 . 1 2 7. . 0.844. . 0.770. . 0.810. . 0.2400 . 2 1 4. . 0.627. . 1 85.98

219.58. . 56.8136.67 57.67 58.05 13752.9 120.0

50591.4921. 4 3 81 . 1 4 21 . 1 3 50.8550 . 8 0 70.8550.2660.2400 . 6 1 11 8 1 . 1 02 1 6 . 1 456.235 6 . 1 757.0857.9813745.41 2 0 . 0

5 0 4 01 . 5 1 81.4621 . 1 5 01 . 1 4 50.8470.7940 . 3 5 10.2770.2510.5351 7 6 . 5 12 1 0 . 6 655.5135.2855.8337.5515753.51 2 0 . 1

50421 . 2 61. 4 5 91 . 1 5 41 . 1 5 00.8320.7610.8200 . 2 8 00.2490.5511 6 9 . 3 5202.7!55.9834.0434.5536.5515769.412 0 . 2

24


28/109

TABLE YD. - BLADE-ELEMENT DATA AT BLADE EDGES FOR ROTOR 53(a) 70 Percent of design speed; reading 3027

R A D ! !R?!23455T69

S?'23L55769

I N24.42225.55922.73320.284I " . 1 7 0U.2321 2 . 1 4 41 1 . - 1 7 51 0 . 6 1 3i B S; \5 8 . ;55.957.!~4.i-3.578.577.575. o73.6

O U T23.76225.06322.3472 0 . 1 9 517.5231 4 . 4 6 01 2 . 5 1 11 1 . 5 9 31 0 . 8 7 6V E lC ' J T1 o . D77.278.987.1195.62.04.52H.O212.2226.3

A B S M A C H N OR?123i5. r*D789

RP123456789

I N0.4740.4990.5530.5280.5400.5*00.5370.5340.525

P E R C E N TS P A N5.001 0 . 0 015-0030.0050.0070.0085.0090.0095.00

C U T0.5220.5280.5340.5590.5850.6130.6340.6390.621

I N CM E A N-3.3-3.6-3.2-2.7- 1 . 30.21 . 11.31.6

A B S!N0.00.00 . 00 . 00.00.- 0 . 0- 0 . 0- 0 . 0

R E LI N259.7258.1253.9244. 3229.82 1 5 . 1204.82 3 1 . 1196.0

B E T A KO U T',0.31 1 . 212.615.322.526.629.450.230.6

V E LO U T240.9255.8229.5214.5194.3185.3183.8163.61 7 8 . 1R E L M A C H N OI N0.7750.7760.7640.7380.6950.6510.6190.6080.592

I D E N C ESS-7.0-7.3-7.1-7.3- 7 i O-6.4-6.0-5.8-5.3

O U T0.7180.7030.6840.6400.5810.5550.5520.5520.536

D E V5.75.65.75.24 V B5.97.78.21 0 . 1

' R E L!K52.45 0 . 048.944.55 9 . C55.929.923.627.5

E E T A XG U T44.442.540.553.22!. 59.4- 0 . 0-5.0-4.5

K E R I D V E LI N1 5 6 . 0165.9167. 1174.9178.5173.5177.5176.6173.8

O U T172.2175.9174.61 7 5 . 5180-.8182.61 8 5 . 8183.4177.5

-/' UI N2S3.2S2.32i2.52S3. 1287.8237.727.8237.6287.7

A L T E M PR A T I O1 . 0 2 31 . 0 2 41 . 0 2 51 . C 2 91 . 0 3 41 . 0 3 51 . 0 3 41 . 0 3 51 . 0 5 0T A N G V E L!\0 . 10.10 . 10.10. 00.-0.0- 0 . 1- 0 . 1

O U T5 1 . 234.339.152.674.89 1 . 61 0 3 . 7106.81 0 5 . 1

H E R I D M A C H N OI N0.4740.4990.5030.5280.5400.5400.5370.5340.525D - r A C T0.1270.1490.1660 . 2 1 10.2690.2640.2300.2130 . 2 1 1

O U T0 . 5 1 30.5180.5210.5360.5400.5480.5520.5520.554EFF0.9000.9831 . 0 1 01.027i ;0201.0221 . 0 1 11 . 0 1 20.921

LOSS C O E F FT O T0.0230.004-0.003-0.009-0.008- 0 . 0 1 0-0.005-0.0060.037

P R O F0.0230.004-0.003-0.009-0.008- 0 . 0 1 0-0.005-0.0060.037

T O T A L - P R E S SI N1 0 . 0 91 0 . 1 31 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 0

R A T I O1.0741.0851 . 09'!1 . 1 0 91 . 1 2 51 . 1 3 11 . 1 2 71 . 1 2 31.099K K E E L S P E E DI N204.9197.81 9 1 . 31 7 0 . 6144.71 1 9 . 9102.296.!90.6

K E R I DV E L R1 . 0 9 01.0481.0451.0271 . 0 1 31.0241.0361.0381 . 0 2 1

O U T199.6193.5188.0169.9146.01 2 1 . 9103.697.19 1 . 1P E A < S SM A C H N O1.0270.9840.9640.8700.7480.6510.6190.6080.592

L O S S P A R A MT O T0.0080 . 0 0 1- 0 . 0 0 1-0.003-0.003-0.003- O. ' OOI- 0 . 0 0 10.008

P R O F0.008o . o o - i- 0 . 0 0 1-0.003-0.003-0.003- 0 . 0 0 1- 0 . 0 0 10.008

25


29/109

TABLE VH.'- Continued,(b) 70 Percent of design speed; reading 3028

R P17345689

R?23i5682

R A D I II N O U T24.422 23.78225.569 23.06322.738 22.34720.234 20.1961 7 . 1 7 0 17.32814.232 14.4601 2 . 1 4 4 1 2 . 3 1 11 1 . 4 7 3 1 1 . 5 9 31 0 . 8 1 3 10.876A B S!N142.81 5 3 . l15! .2156.3159.85 5 8 . 7155.7

155.353.5

V E LO l ' T162.8155.2167.0172. 1'". 3182.618'. 5188.8185.1A B S M A C K N O

R?23z5639

R ?23z56T89

; N0.4270.4500.4530.47!0.4310.4770.47!0.4700.451P E R C E N TS P A N5. 0

j t i15.5 1 .5:-.. .CO.C" 19 5 . 0

O U T0.4310.4S30.4940 . 5 1 00.5260.5430.5590.5530.555

I N CM E A N-5.5-S.8-0.50. 51.73.24.14.54.7

A B SI N-0.0-0.0-0.0-0.0-0.0-0.0- C . O-0.0-0.0R E LI N249.4243.0242.8231.!215.01 ? . 5185.7183.41 7 8 . 1

B E T A MO U T17.517.418.02 1 . 426.629.632.733.333.9

V E LO U T215.9213.4208.61 9 2 . 11 7 1 . 61 6 1 . 7157.9158.0154.1

R E L K A C H N OI N0.7450.7430.7230.6940.6470.5970.5610.5510.535

I D E N C ESS-4.2-4.6-4.5-4.3-4.0-3.4-2.9-2.8-2.4

C U T0.6370.6300.6170.5690.5090.4810.47!0.4720.460D E V5.45.55.75.55.87.58.38.81 0 . 0

'RELI N55.152.851.547.342.036.953.031.630.5M E R I DI N142.81 5 0 . 11 5 1 . 2156.8159.8158.7155.7

156.3153.5M E R I D K A

I N2.4270.4500.4530.4713.4810.4770.47!0.4700.461D - F A C T0.2290.2330.2330.2810 . 3 3 50.5190.29!0.2720.263

B E T A M -O U T44.042.440.435.522.51 1 . 0 "0.6-2.4-4.7V E LC U T155.2157.7!53.91 6 S . 2153.51 5 3 . 3157.9157.9155.6

C H N OO U T0.453S.4550.4710.4740.4700.472

0.47!0.47!0.459

EFF0 . 9 1 10.6871 . 0 2 31 . 0 3 21.149 . v" 1 . C 5 21 . G 3 !0.962

T O T A L T E M PI N R A T I O288.7 1.035238.7 1.055288.5 1.034236.0 .036287.9 1.035287.9 1.034287.9 1.033287.9 1.032237:9 1 . 0 2 9 "T A X G V E L!M- 0 . 1- 0 . 1

- 0 . 1- 0 . 1- 0 . 1- 0 . 1- 0 . 1- 0 . 1- 0 . 1

LOSS'. \J i0 . 0 3 30. 15- C . 1 1 * . * ~ 7- : . 2 4~t.w-C. '.9- 0 . 1 3

C U T49.049.35 1 . 562.979.4.90.21 0 1 . 2103.51 0 3 . 3

C C E F FP R O F.033.C05- .01!- .017- .024~ . j2S- .019- 0 . 0 1 30 . 0 2 1

T O T A LI N1 0 . 0 91 0 . 1 31 0 . 1 31 0 / 1 31 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 - 0 . 1 1W H E E LI N204.4

197.3189.9169.6143.81 1 9 . 11 0 1 . 596.090.2K E R I D

. V E L R' .0371 . 0 5 01 . 05!1 . 0 2 10 . 9921 .0001 . 0 0 81 . 0 1 01 . 0 0 1

PRESSR A T I O1 . 1 1 61 . 1 2 51 . 1 3 01 . 1 3 71 . 1 3 81 . 1 3 21 . 1 2 51 . 1 1 91 . 02 .S P E E DC U T1 9 9 . 11 9 3 . 1186.6168.91 4 5 . 11 2 1 . 1102.997.090.7

P E A K S SM A C K N O1 . 5 5 3i . o ; s0.9370.3990.7340.6670.5700.5510.535

L O S S P A R A MT O T0 . 0 1 2O . C C 2- 0 . 0 0 4-0.005- O . C 0 6-0.008-0.005- 0 . 0 0 40 . 0 0 5

P R O F0 . 0 1 20.002-0.004-0.006-0.008-0.008-0.005-0.0040.005

26


30/109

TABLE VH. - Continued,(c) 70 Percent of design speed; reading 3029

R A D 1 1R P123i55789

R?\23455T35

I N24.42223.56922.73820.2841 7 . 1 7 014.2321 2 . 1 4 411.4731 0 . 8 1 3

A B S!N128.6134.7135.314!.;142.81 4 1 .61 4 0 . :135.2136.6

232322201 71 41 21 11 0

O U T.782.063.347.196.328.460. 3 1 1.593,876V E L;;1**\'

O U T56.257.055.659.562.565.471.57 1 . 370.8

A B S M A C H N OR?;23456*39

R?123456T0O9

I N0.3350.4020 . 4 3 40.4220.4270.4240.4190.4160 . 4 C 3P E R C E N TS P A N5. 01 0 . 01 5 . 03 0 . 05 3 . 07 * r . r;3 5 ! o o- 0 . 0 09 s ! o o

000r< j M ior,w00

C U T.458.451.450.470.430.492.509.5C8.507

; N C ;K E A \2.32.12.53.24.96.57.27.4

ABSI N-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0-0.0

R E LI N241.6238.6255.2220.3202.635.375.269.2165.3R E L M AI N0.7200 . 7 1 2.696.659.0.6050.5540.5:30.5060.439

D E N C Es s-1.4- 1 . 7-1.4- 1 . 4- o . e-0.50.13 3y J0. 6

B E T A KO U T25.022.422.926.250.335.335.836.437.3

V E LO U T199.3'95.71 5 1 . 4173.6153.8142.11 3 9 . 1137.7136.5CH NOO U T0. 5850.5730 . 5 6 20 . 5 1 10.4543.4210.4130.4050.405D E V5.25.66.46.57.4.48.90 /9'. 3

R E LI N57.955.554.650.245.240.135.034.733.5

X E R I D!N12S.6134.7135.31 4 1 . 0142.8141.61 4 0 . 0139.21 35.5

B E T A XC U T45.342.54 1 . 134.424.212.01 . 2- 1 . 8-5.5V E LO l ' T 143.

145.1144.3VS. 3': 40.41 3 5 . 1 '1 3 5 . ;137.1 3 5 . 5

T O T A L T E M P! N R A T I O238.6 1.043286.5 1.0422SS.4 1.04123.0' 1.3402 E 3 . 0 ',."3332 & S . O 1.0552S7.9 1.034267.5 1.032237.5 1.030T A N G V E LN C U T- . i . ;59.9- . '0 . 9- . 70.4- . 81.95'.5- . '.00.4- . 101.6- 0 . 103.5

X E R i D K A C H N OI N0.3350.4020 . 4 0 40.4220.42~0.4240 . 4 1 50 . 4 1 50 . 4 0 3

D - F A C T0.2975 . 2 3*.2i>B0.3440.3S4G . 3 7 S0.342& 5'&* J tC . 3 0 7

O ' J TC.4220.4250.424.422.4:4L' '.4:30 . 4 0 S

T O T A LI N1 0 .1 0 .1 0 .1 0 .1 0 .1 0 .1 0 .1 0 .1 0 .

1 01 314141 414/1 51 1

W H E E Li204953959431 90 19690

' t ^ r ;V E L. !. < j

M ..5.8.9>. 6f \'.k 2! sI DX1 377.067.0

: . C'. 3.9.9

: S332293c c -0 . 4 0 4 0.955

P R E S SR A T I O1 . 1 5 01.1551 . 1 5 51 . 1 5 11 . 1 4 51.1341 .1241 . 1 1 51 . 1 0 6S P E E DC U T99. '92.635. 8 - . 444.920.503.297.290.8

?EA'< SSM A C n \C'.0351.044: . 0 1 9O . S 2 2o . e o s0.6520.6130.530.558

E r r _ ; s s :;zr _ c s s P A R A X .0 . ^5 5O-.'-iSl . : ' . .* ~. 35T /

Tf " "/. . s ai

~ Z R ~. 22 . 22" 2 . 02- . 07 - . C7- . '. 7 - . ".7- . 2 0 - . 2 022 - . 22- . O J - . 0 5

O . J i S 0.02o

T O Ti .C .- C ._A

- C .- 0 .- 0 .A F

0.0

8

5TO2r , 106

P R C T0 . 0 0 8o . o o :-0.0-C2-0.006-0.007- 0 . 0 0 6- 0 . 0 0 20 . 0 0 10.006

27


31/109

TABLE VH. - Continued,(d) 70 Percent of design speed; reading 3030

R P!2r456.789

R P'3455"S^

R A D: \2 4 . 4 2 : -2:-.5o~22. 720.2S4* 7 '"'*'14 '.252' 2 ' * * * 1 1 . 4 7 31 0 . 6 1 3

A 5 S; Ni 1 2 . 5' t ."i*' = - . 5 ^ - * * '25.3' 24 . ''22.5i " 2 . C" "9.7

, ty/j .2 5. 7 223.;53" " 34720 . l i ' 61 7 . J 2 21 4 . 4 5 C -< > ~ , ' \

1 1 . 5 9 31 0 . 7 6

V E ~ l ; T

1 t " ^

1 4 3 . 745'. 315; .4' C * n.1 5 5 . 91 5 E . 6'57.9159.6

A 3 S X A C H N OR?23456*89

R?!23456789

I N0.354C . 5 5 30.5560.37C0.3730.37:0.3550.5530.556P E R C E N TS P A N5.001 0 . 0 01 5 . 0 03 0 . 0 050.007 0 . 0 085.009 0 . 0 095.00

C U TG.4260.4540.4330.44C0.4430.4530.4690.4670.475

A B SN- .- .- .- .- .- .- o l- 0 .

R E L: N233.2 3 0 . :2 2 5 ' . !- > J -9 1 .2 i^* v59.655.650.3

3CTAXc u :29. 923.52 S . S3 1 . 935.73'. 94; . '.4 0 . 541.4V E Lr \ ;Ti - e ! s-8.5"4.055.135.624.321.62 0 . 11 2 0 . 7

R E L K A C H N OI N0.5920.5S40.6700.6260.5700 . 5 1 30.4750.4530.447

I N C I D E N C EM E A N5.55.45.96.98.71 0 . 21 1 . 01 1 . 01 1 . 4

s s1 . 81.62.02.33.03.63.93.94.3

O U T0.5200.5210 . 5 0 90.4570.3980.3650.3590.3550.557

D E V6.16.07.07.28.48.98.48.87.8

;'.\

_;*

r v ^ _ L I N ' . ':'.;5".i53.94t. '.43.959.953.357.2

K E R i D'\1 2 . 5 '.1 3 . 71 9 . 52 4 . 125.32 4 . 122.51 2 2 . 0 1l 1 9 . 7 '.K E R I D M A C0Crk >c00to0

I N.354 0.355 0.356 0.37& 0.373 0.370 0.355 0- 3 t i 3 0.356 0D-FACT000000000

.385 0

.369 C.37! 0. 4 1 5 0.454 C.440 0.399 0.384 0.353 0

' ' 'i u *-4.6

" I '/ * 3 5 . '25.2i J , i.' "- 2 . 5-6.3

v ' r'CU T26.-~ * 29.92T.522.-2T.'52 1 . 520. D1 9 . 6r NGO U T.369.332.330.374.550.558.359.355.354

E F F.681.958.982.995.997.996.990.967.970

* ~.

^- . C211.:; i - ^ . ^2ii. '.2'li. C ~ . * j~ - - *257. 9257.9

7N- . ;- . :- . - . - ,- . i- . j- . - 0 . 1- 0 . 1

L O S ST O T0.0740.0260 . 0 1 10 . 0 0 30 . 0 0 20 . 0 0 30.0080.0270.025

A L TEX?R A T I O. Zi* " '. ~ . 0-.042.032.055.0351 . 0 3 2

N G V E LO U T72.97 1 . 1T i l s79.583.094.6102.21 0 2 . 61 0 5 . 7

C O E F FP R O F0.074C.0260 . 0 1 10 . 0 0 30.0020 . 0 0 30.0080.0270.025

T 0 7 AI N1 0 . 1 01 0 . 1 31 C . 1 31 0 . 1 41 C . 1 41 0 . 1 41 0 . 1 41 0 . 1 31 0 . 1 !

. PRESSR A ' i C.' v.

1 . 77; ! 7 71. 701 . 5 51 . 5 51 . 251 . 1 61 . 1 1 !

W H E E L SPEED-I N2 0 4 . 01 S 5 . 91 9 0 . 71 7 0 . 11 4 4 . 31 1 9 . 3102.295.490.8M E R 1 DV E L R1 . 1 2 51 . 1 0 01.0871 . 0 2 80.9790-.9790.9920.9841 . 0 0 1

C U T1 5 3 . 71 9 2 . 71 6 7 . 41 6 9 . 4145.71 2 1 . 2103.697.4S I . 3

P E A K S SM A C H N O1 . 1 2 41 . 0 7 91 . 0 5 60.9580.8360.7130.6320.5040.577

L O S S P A R A MT O T0.0260.0090.004-0 . 0 0 10.00!0.00!0.0020.0060.006

P R O F0.0260.0090.0040 . 0 0 10 . 0 0 10 . 0 0 10.0020.0060.006

28


32/109

TABLE VH. - Continued,(e) 70 Percent of design speed; reading 3031

R A D ! !R Pl23456189

R Pt232.56"*39

I N2-5.42223.56922.73820.2841 7 . 1 7 014.23212.1"1 1 . 4 7 31 0 . 8 1 3A B SI N93.498.5' 59.42 3 . 5C 5 . 5,5.90 5 . :3 4 . 8D 5 . C -

O U T23.78223.06322.3472 0 . 1 9 617.3281 4.4601 2 . 3 1 11 1 . 5 9 31 0.876V E LO U T1 3 5 . !'.5T.'.1 3 9 . 51 4 2 . 5!4!.91 4 5 . 51 4 9 . 3149.41 5 C . 8

A B S M A C H N OR P123456789

R P123i56789

i \0.276C.2S20.2540.3080 . 3 1 50 . 5 1 40 . 5 1 20 . 3 1 10.306

P E R C E N TS P A N5.001 0 . 0 01 5 . 0 03 0 . 0050.0070.0085.0090.0095.00

O U T0.3900.3970.4070 . 4 1 50 . 4 1 50.4270.4400 . 4 4 10.445

A B SI N- 0 . 0- 0 . 0- 0 . 0- 0 . 0- 0 . 0- 0 . 0- 0 . 0- 0 . 0- 0 . 0R E XI N225.32 2 1 . 12 1 5 . 51 9 9 . 71 7 6 . 9'59.71 4 G . 2

142. !'.37.1

B E T A MO U T46.938.636.838.54 1 . 742.54 3 . 143.444.2

V E LC U T1 3 6 . 71 5 2 . 21 5 2 . 91 3 7 . 91 7.7'.09.81 0 9 . 01 0 8 . 71 0 9 . 0R E L K A C H N OI N

0.6670.6550.6380.5930 . 5 3 10.4740.4340.4220.407

I N C I D E N C EM E A N9.91 0 . 01 0 . 51 1 . 71 3 . 41 4 . 81 5 . 21 5 . 21 5 . 6

SS6.26.26.67 .17.78 . 18 . 18 .18.4

O U T0.3550.44!0.4440.4020.3440.3220 . 3 2 10 . 3 2 10.322

D E V8.98.38.28.19.08.78.28.27.2

11

R E LI N65.563.562.558.653.748.544.042.54 1 . 3

K : R I D!N9 5 . 496.599.40 3 . 50 5 . 91 0 5 . 51t

3 5 . 10 4 . 81 0 3 . 0

B E T A KO U T47.645.242.93 5 . 025.81 2 . 20.5- 3 . 0- 7 . 5

y r . LO U T92.21 0 7 . 21 1 2 . 11 1 1 . 51 0 6 . 01 Q 7 . 51 0 9 . 0I D S . 51 0 8 . 1

T O T A LI N288.5288.4283.32 8 8 . 1288.0288.0288.0288.0288.0T A N GI N- 0 . 0- 0 . 1- 0 . 0- 0 . 1- 0 . 1- 0 . 1- 0 . 1- 0 . 1- 0 . 1

T E M PR A T I O1 . 0 6 61 . 0 6 01 . 0 5 61 . 0 5 21 . 0 4 51.0401 . 0 3 51 . 0 3 31 . 0 3 2V E LC U T5 8 . 7S5.585.888.794.55 3 . 21 0 2 . 11 0 2 . 71 0 5 . 2

K E R i D K A C H N Or -u0000D000

i N.276.292.294. 3 0 8. 3 1 5. 3 1 4. 3 1 2. 3 1 1. 3 0 6

D - F A C T00000000- 0

.604.495.467.493.525.494. 4 3 0.406.375

O U T0.26S0 . 5 1 10.3260.3250 . 3 1 00 . 5 1 50 . 3 2 10.320C . 5 1 9E F FO.S650.7850.6590.9056 . 9 3 10.9460.9780.9730.970

L O S S C O E F FT O T -Q.25&0 . 1 6 70 . 1 0 70.0790.0600.0520.0220.0260 . 0 3 0

P R O F0.2560 . 1 6 70 . 1 0 70.079'0.0600.0520.0220.0260.030

T O T A LI N1 0 . 1 11 0 . 1 31 0 . 1 31 0 . 1 31 0 : 1 310.141 0 . 1 31 0 . 1 31 0 . 1 2

W H E E LI N205.0197.81 9 1 . 11 7 0 . 51 4 4 . 11 1 9 . 51 0 1 . 695.09 0 . 5K E R I DV E L R0.5881 . 0 8 8. 1 2 8. 0 7 3. 0 0 0. 0 1 4.037.0371 . 0 5 0

P R E S SR A T I ' D1 . 1 6 81 . 1 7 31 . 1 7 81 . 1 7 31 . 1 5 51 . 1 4 01 . 1 2 61 . 1 1 81 . 1 1 2S P E E DO U T1 9 9 . 61 5 3 . 61 8 7 . 81 6 9 . 81 4 5 . 5121 .41 0 3 . 097.09 1 . 0

P E A K S SK A C K N O1 . 1 8 31 . 1 3 61 . 1 0 70.9990.8630.7550.6400 . 6 1 10.584

L O S S P A R A MT O T0.0840.0550.0360.026.0.0190 . 0 1 50.0050.0060.007

P R O F0.0840.0560.0360.0260 . 0 1 90.0.150.0050.0060.007

29


33/109

TABLE VH. - Continued,(f) 80 Percent of design speed; reading 3011

R A D I IR P123i56"*e9

R PI>345c"*8C *

' I N24.42223.56922.75820.2841 7 . 1 7 0U.2321 2 . 1 4 41 1 . 4 7 31 0 . 8 1 3

A B SI N5 7 1 . 2179.5!83.5183.01 9 1 . 8191.8189.0188.7185.5

O U T23.78223.05322.3472 0 . 1 9 517 . 3 2 814.4601 2 . 3 1 11 1 . 5 9 31 0.876V E LO U T190.21 9 1 . 8194.22 0 1 . 4209.4214.6220.5221.7215.7

A B S M A C H N OR?123I5e789

RP123456789

I N0.5160.5420.5460.5720.5830.5800.5740.5730.563

P E R C E N TS P A N5.00 10.0015.0030.0050.0070.0085.0090.0095.00

O U T0.5640.5680.5760.5990.6240.6420.6610.6660.648

A B SI N0.00.00 .00. 00.00.00.00.00.0

R E L I N290.7288.8283.5271.3253.0254.6222.0218.6212.7

B E T A MO U T16.- 1 6 .17 .2 1 .26.29.32.32.33.

V E LO U T252.8247.22 4 1 . 4222.92 0 1 . 3190.2186.6186,4180.6

599453295

R E L M A C H N OI N0.8750.8720.8570.8230.7690.7130.6740.6640.645

I N C I D E N C EM E A N- 1 . 7-2.0- 1 . 6- 1 . 00.41.92.83.03.5

SS-5.4-5.8-5.5-5.6-5.3-4.7-4.3-4.1-3.7

O U T0.7490.7330 . 7 1 60.6620.6000.5690.5600.5600.542

D E V5.25.25.34.84.66.88.08.51 0 . 1

R E L' I N53.95 1 . 550.445.9 .40.735.63 1 . 730.329.2

M E R I DI N1 7 1 . 2179.5180.6188.61 9 1 . 81 9 0 . 8189.0188.7185.6

B E T A MCUT43.8- 4 2 . 140.032.72 1 . 31 0 . 3' 0 . 5-2.7-4.5

V E LO U T182.4183.5184.8187.5187.5187.2186.6186.21 8 0 . 0

T O T A L T E M PI N2S3.9238.8286.7288.1"287.8287.7287.7287.7287.7

R A T I O1.0431 . 0 4 5.045.048.050.047.045.044.040

T A N G V E LI N0 . 10 ' . 10 . 1O . I0 . 10 . 10/ 1 0 . 10.2

O U T53.955.859.673.693.4-104.91 1 7 . 4120.41 1 8 . 9

M E R I D M A C H N OI N0.5160.5420.5460.5720.5830.5800.5740.5730.563D - F A C T0.2200.234.0.244.0.2900.3350.3210.2920.2770.275

O U T0.5410.5440.5480.5570.5590.5600.5600.-5590.540E F F0.9300.9691.0051.0091 . 0 1 20.9940.9710.9510.860

L O S S C O E F FT O T0.0250 . 0 1 2-0.002- 0 . 0 0 4-0.0060 . 0 0 30 . 0 1 70.0280.077

P R O F0.0250 . 0 1 2- 0 . 0 0 2- 0 . 0 0 4-0.0060 . 0 0 30 . 0 1 70.0280.077

T O T A L P R E S SI N1 0 . 0 91 0 / 1 31 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 0

R A T I O.148. 1 6 0.168. 1 8 0.187.173.162.153.126

W H E E L S P E E DI N235.0226.3218.6195.0165.1136.71 1 6 . 61 1 0 . 51 0 4 . 0

M E R I DV E L R1.0661.0221.0230.9940.9770.9810.9880.9860.970

O U T228.9221.52 1 4 ; 9194.2166.6138.91 1 8 . 21 1 1 . 6104.6P E A < S SM A C H N O1.2071 . 1 5 51 . 1 3 01.0250.8910.7430.6740.6640.645

L O S S P A R A MT O T0.0090.004- 0 . 0 0 1- 0 . 0 0 1-O'.OOZ0 . 0 0 10.0040.0070 . 0 1 7

P R O F0 . 0 0 90.004- 0 . 0 0 1- 0 . 0 0 1-0.002" 0 . 0 0 10.0040.0070 . 0 1 7

3 0


34/109

TABLE VH. - Continued,(g) 80 Percent of design speed; reading 3012

. R A D I IR P123t56789

R P\>345632

I N24.42223.56922.73820.2841 7 . 1 7 014.2321 2 . 1 4 41 1 . 4 7 31 0 . 8 1 3A B S!N57.065. 667.1

-4.475.574.5"2.371.357.0

O U T23.78223.06322.3472 0 . 1 9 617.3261 4.4601 2 . 3 1 11 1 . 5 9 31 0 . 8 7 6

V E LC U T1 8 2 . 1164.4!64.3!89.9:93.81SS.4204.62 0 4 . 5202.8

A B S M A C H N OR P123456789

R P123i.56789

I N0.4730.4580.5030.5270.5330.5280.5220.5170.505

P E R C E N TS P A N5.001 0 . 0 015.0030.0050.0070.0065.00. 9 0 . 0 095.00

O U T0.5360.5430.5440.5610.5740.5930.6100.6090.599

A B SI N0 . 10.00.0.0.0.0.0.. 0.R E L!N282.9260.4275,02 6 1 . 72 4 1 . 7222.0208.7205.8197.4

B E T A MO U T2 1 . 72 1 . 421.924.829.432.134.835.536.3

V E LO U T233.9230.8223.2207.1135.41 7 2 . 1167 '.9166.2!62.5R E L M A C H N OI N0.8490.8430.8280.7900.7310.6710.6300.6150.595

I N C I D E N C EM E A N0.50.30.61 . 22.84.45.25.56.'1

SS-3.2-3.5-5.4-3.4-2.9-2.2- 1 . 8- 1 . 6- 1 . 0

C U T0.6880.6790.6630.6120.5430.5120.5010.4960.485

D E Y5.05 .15.75.76.37.78.38.99.8

R E LI N56.153.852.646.245.23 8 . 13 4 . 152.83 1 . 9H E R I D: N',57. S165.6167.!

174.4176.5'74.6: 7 2 . e1 7 1 . 5167.6

B E T A MC U T43.742.040.453.723.01 1 . 20.6-2.4-4.9

V E LC U T69.27 1 . 6" i .572.45S.G'~ ("> Coa.b67.9 5 . i5 1 . 9

T O T A L T E M PI N288.9283.8238.62 G 8 . 0287.8237.8287.3287. S287.9

R A T I O.054.053.053.053.051.046.045.043.040

T i N G \'EL; N0.!i - ' . '0.23 . 20.20 . 20.20.20.2

C U T67.5'67.368-. 979.695.2i o a . ;1 ' 6 . 91 1 3 . 5I i 8 . 7K E R I D M A C H N OI N0.4730.4980 . 5 C 30.5270.553 .0.5280.5220.5170 . 5 G 5D - F A C T0.2880.2890.2950.3340 . 5 3 C0.5650.3360.5220 . 3 1 0

0000fl0000

011111000

O U T.497.505.505.509.500.5C2.50!.495.483E F F.932'. C C 5.009. 0 1 0.015.02!.989.972. 9 1 0

L O S S C O E F FT O T0.029- C . 0 0 2- 0 . 0 0 4- 0 . 0 0 5- 0 . 0 0 6-0.0!50 . 0 0 70 . 0 1 70.057

P R C F0.029- 0 . 0 0 2-0.004-0.005- 0 . 0 0 8- 0 . 0 1 30.0070 . 0 1 70.057

T O T A LI N1 0 . 0 91 0 . 1 31 0 . 1 31 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 51 0 . 1 0W H E E LI N235.1226.4

2 1 3 . 5165.3!65.5137.2f - T *1 1 1 . 11 1 0 . 6104.4

H E R I DV E L R -1 . 0 7 31 . 0 5 71.0260:9880.957.0.9670.9720.9690.966

P R E S SR A T I O1 .1871.2001 . 1 9 91 . 2 0 01 . 1 9 21 . 1 8 01 . 1 6 51 . 1 5 31 . 1 3 5

S P E E DO U T223.9221.62 1 4 . 7194.4167.0!59.4M8. 81 1 1 . 71 0 5 . 3

P E A K S SM A C H \01.235!.!84!.!541.0510.9(90.7870.6890.6540.627

L O S S P A R A KT O To . o ; o- 0 . 0 0 !-0.002-0.002-0.003-0.004O . C 0 20 . 0 0 40 . 0 1 3

P R O F0 . 0 1 0- 0 . 0 0 1-0.002- 0 . 0 0 2- 0 . 0 0 3-0.0040.0020.0040 . 0 1 3

31


35/109

TABLE VH. - Continued,(h) 80 Percent of design speed; reading 3014

R P12345689

R P12345539

R A D I!IN OUT2* . -122 23.7622 3 . 5 3 9 2 3 . 0 5 32 2 .758 2 2 .34 72 0 . 2 6 4 2 0 . 1 9 51 7 . 1 7 0 17.32 814 .2 32 1 4 .4 6 012 . 14 41 1 . 4 7 31 0 . 8 1 3

iBSIN1 4 5 . 3152.41 5 3 . 0!59.5lo l .o! 5 3 . 51 5 7 . 3156.9',54.1

1 2 .3 1 11 1 . 5 9 310.876

V E LO U T1 7 6 . 0175 . 91 7 5 . 5I 7 Q . 7'82.11 8 S . 21 9 2 . 01 9 3 . 9189.2

A B S M A C H N ORP!23i.567e9RPI234567e9

IN0 .4 350 .4 570.4-590. 48 00.4850 .4 790.4730 . 4 7 10 .4 63

PERCENTS P A N5 . 0 01 0 . 0 01 5 . 0 03 0 . 0 05 0 . 0 07 0 . 0 085 .0 090 .0 09 5 . 0 0

O U T0 . 5 1 40 . 5 1 80 . 5 1 70 .52 80 . 5 3 60 . 5 5 10. 5 7 00 . 5 5 70 . 5 5 2

A B SIN0 . 10 . 10 . 10 . 10 . 10 . 10 . 10 . 10 . 1

RE L!N2 7 6 . 02 7 3 . 22 66.82 52 .02 3 0 . 92 1 0 . 0195 . 9191.7165.9

B E T A MO U T26.62 5 . 725.928.73 2 . 93 5 . 23 7 . 33 3 . 23 8 . 9

V E LO U T2 1 7 . 32 1 5 . 82 1 0 . 21 9 1 . 21 6 7 . 1155.5152.7150.2147.9

R E L M A C H N OIN0.8250 . 8 1 90 . 8 0 00 . 7 5 80 .6950 . 6 3 10 . 5 8 90 .5760 . 5 5 8

INC IDENCEM E A N2.62.53.03.75.36.97.77.88.3

S S-1.1-1.3-0.9-0.9-0.40.30.70.71 . 1

O U T0 .6350 . 6 3 10 . 6160 .5620.4930 . 4 6 00 . 4 5 30 . 4 4 60 . 440

D E V4.95.56.26.57 . 18.38.58.79.2

R E L B E T A MI N O U T53.2 43.65 6 . 1 42.45 5 . 0 41 .05 0 . 7 34.44 5 . 6 23.94 0 . 6 11.33 5 . 63 5 . 13 4 . 0

M E R !IN1 4 5 . 3152 . 41 5 3 . 0159 . 51 6 1 . 61 5 9 . 3157.3156.91 5 4 . 1

0 . 8-2.5-5.5

D V E LC U T1 5 7 . 41 5 9 . 51 5 6 . 81 5 7 . 7152 . 8152.2152.7150 . ;14 7 . 3

T O T A L T E M PI N R A T I O2 3 3 . 8 1.0632 S S . 7 1.0612 3 8 . 6 1.0602 8 7 . 9 1.0572 8 7 . 9 1.0532 8 7 . 9 1.0492 87.92 8 7 . 82 87.9111

T A N i GIN0 . 2C . 20 . 20 . 20 . 20 . 20 . 20.20 . 2

. 0 4 5. 0 4 2. 0 4 0 '

V E LO U T78. 976 . 677 . 286.29 8 . 91 0 7 . 31!1

16.318.018 . 8M E R ID M A C H N OIN

0 . 4 3 50 . 4 5 70 . 4 5 90 . 4 8 00 .4 860 . 4 7 90 .4 730 . 4 7 10 . 4 6 3D - F A C T0 . 3 5 00 . 3 4 10 . 3 4 30 .3820 .4 2 70 . 4 1 00 . 3 6 90 . 3 6 20 .34 6

O U T0 . 4 6 00 . 4 6 70 .4 650 . 4 6 30 . 4 5 00 . 4 5 00 . 4 5 30 . 4 4 60 . 4 3 8

EFF0.9220 . 9 7 30.9941 . 0 0 81 . 0 1 01 . 0 0 20 . 9 9 90.9760 . 9 3 0

L O S S C O E F FT O T0 . 0 4 40 . 0 1 50 . 0 0 3- 0 / 0 0 5- 0 . 0 0 6- 0 . 0 0 20 . 0 0 10 . 0 1 70 . 0 4 9

P R O F000-0-0-0000

. 0 4 4.015

. 0 0 3.005. 0 0 6. 0 0 2. 0 0 1.017. 0 4 9

T O T A LIN1 0 . 1 01 0 . 1 51 0 . 1 31 0 . 1 41 0 . 1 41 0 . 1 41 0 - . 1 41 0 . 1 41 0 . 1 1

W H E E LW2 3 4 . 82 2 6.92 18. 7195 . 21 6 5 . 11 3 7 . 01 1 6 . 91 1 0 . 31 0 4 . 1M E R IDV EL R1. 0 831 . 0 4 61 .0380 . 9 8 90 .94 60 . 9 5 50 . 9 7 10 .9570 . 9 5 6

P R E S SR A T I O1 . 2 1 81 2241. 2 2 3. 1 . 21 71 . 1 9 91 . 1 8 21 . 1 6 71 . 1 5 31 . 1 3 7

S P E E DO U T2 2 8 . 72 2 2 .02 1 5 . 01 94 . 3166.6139 . 21 1 8 . 6111.51 0 4 . 7P E A K S SM A C H N O

1.2601. 2 141 . 1 8 31 . 0 740 . 9 3 60 . 8 0 40 . 7 1 00.6780 . 6 5 0

L O S S P A R A MT O T0 . 0 1 60 . 0 0 50 . 0 0 1- 0 . 0 0 2- 0 . 0 0 2- 0 . 0 0 00 . 0 0 00 . 0 0 40 . 0 1 1

P R O F0 . 0 1 50 . 0 0 50 . 0 0 1- 0 . 0 0 2- 0 . 0 0 2- 0 . 0 0 00 . 0 0 00 . 0 0 40 . 0 1 1

32


36/109

TABLE vn. -Continued,(i) 80 Percent of design speed; reading 3015

R A D I IRPt23i56789

RP123i5689

IN24.4222 3 . 5 6 92 2 .7382 0 .2 8417.170U.23212. 14411.47310 . 813A B SIN134.2140.2

141.2!47.0148.0145.4144.6143.7! 4 0 .7

O U T23.78223.06322.34720.19617.32814.46012 . 31111.59310.876

V E LO U T169.2171.41 7 0 . 0172.2173.2I 1 8 K 2180.5!82.2

A B S M A C H N ORP123A56789

R P123i55789

IN0 . 4 0 00 .4 1 90.4220.4400.4440.4390.4330.4300.421

PE R C E N TS P A N5.001 0 . 0 0

1 5 . 0 030". 0050.0070.0085.0090.0095.00

O U T0.49 20 . 4 9 90.49 50 . 5 0 40 . 5 0 80 .52 20 . 5 3 60 . 5 3 40 . 54 0

A B SIN0.0.0.0 .0.0 . 10 . 10 . 10 . 1RELIN2 7 0 . 92 6 6 . 72 6 0 . 4

244.4221.9200.6185.8181.2174.9

B E T A MO U T3 0 .29.29.32.36.3 8.4 0 .4 0 .41.

V E LO U T203.8204.1198.0177.4153.8142.3138.7137.11 3 8 . 0

815532172

R E L M A C H N OIN0.8080.7970.7790.7320.6650 . 6 0 10.5560.5420.523

I N C I D E N C EM E A N4.74.75.26.07.89.41 0 . 010 .21 0 . 7

S S1 . 00 . 91. 21.42.12.83 . 03.13.6

O U T0.5920.5940.5770.5190.4510 . 4 - 90 .4 1 00 . 4 0 60 . 4 0 9

D E V5.85.96.97.28 . 08.68.58.78.3

RE LIN60.35 8 .357.25 3 . 048.24 3 . 13 8 .93 7 .536.5

M E R I DIN134.2140.2141.2147.0148.0146.4144.6145.71 4 0 . 7

B E T A MO U T44.542.841.735.124.81 2. 10 . 8-2.5-6.3V E LO U T

145.41 49 . 71 4 8 .0145.2139.71 3 9 . 1138.7136.91 3 7 .1

T O T A LIN2 8 8 . 72 88.62 88.42 8 8 . 0287. 92 87.92 87.92 87.92 87.9T A N GIN

0 . - . 10 . 10 . 20 . 20 . 10.20 . 20.2O . I

T E M PR A T I O1 .0711 .0 6 81.0651.061.055.0 5 1.046.043.042

V E LO U T86.68 3 . 483 .692.6102.51 0 9 . 5116.6117.61 2 0 . 0M E R I D M A C H N O

IN0 . 4 0 00.4190.4220.4400.4440.4390.4330.4300.42!

D - F A C T0 . 4 0 20 . 3 8 10 . 3 3 50 . 4 3 00.4700 .4 5 !0 .4 1 !0 . 3 9 70 . 3 5 5

O U T0.4220 . 4 3 60 . 4 3 10.4250 . 4 1 00 . 4 1 00 . 4 1 00 . 4 0 50 . 4 0 6

EF F0 .876O . S 5 20 . 9 S 3O . S 3 50 . 9 S 30 . 9 8 i0 .9 7 10.9 5 00 . 9 5 5

L O S S ' C O E F FT O T0 . 0800 . 0 3 10 . 0200 . 0 1 00 . 0 0 50 . 0 1 50.0230 . 0 4 00 . 0 5 4

P R O F0 . 0 7 90 . 0 5 10 . 0 2 00 . 0 1 00 . 0 0 50 . 0 1 50 . 0 2 50 . 0 4 00 . 0 5 4

T O T A LIN1 0 . 1 01 0 . 1 31 0 . 1 31 0 . 1 41 0 .1 41 0 . 1 41 0 . 1 41 0 . 1 31 0 . 1 0

W H E E LI N '2 3 5 . 5227-. 02 1 9 . 0195.4165.4137.51 1 6 .9110.5104.2MERIDV E L R1.0841.0671 .0 4 80 . 9880 . 94 40 . 9 5 10 . 9590 . 9 5 50 .9 7 5

P R E S SR A T I O.255.244.259.228.206.185.164.1 5 1.144

S P E E DO U T2 2 9.3222.2215.2194.6166.9159.5118.5111.7104.8P E A K S SMAC'r i NO

1.2901 . 2411.208

.0960.9550 . 8 1 90.7210.6900.661

L O S S P A R A > iT O T0 . 0 2 80 . 0 1 10 . 0 0 70 . 0 0 30 . 0 0 20 . 0 0 40 . 0 0 60 . 0 0 90 . 0 1 2

P R O F0.0280 . 0 1 !O . O G 70 . 0 0 30 . 0 0 20 . 0 0 40 . 0 0 60.0090 . 0 1 2

3 3


37/109

TABLE vn. -Continued,(j) 80 Percent of design speed; reading 3007

R A D ! ! A S S B E T A M R E L B E T A M D I A L P R E S SR P 'I23*5to7e9

R? '1234568^

IN2^.4222 5 . 5 6 9 '2 2 . 7 3 82 0 .2 8 41 7 . 1 7 01 4 .2 5 21 2 . 1 4 41 1 . 4 7 31 0 . 8 1 3A B S; N122.8128.5129.9!3s!'!' ?o.o' 35. 71 3 4 .21 3 2 .?13:. 3

O U T23 .7 8 2 2 3 . 0 S 32 2 . 3 4 72 0 . 1 9 51 7 .5 2 81 4 .4 5 01 2 . 5 1 11 1 . 5 9 31 0 .8 7 6V E LO U T' 6 3 . 6164.5165.116". 2! ~r. fD. i 1 7 2 .11 7 4 .8174.6175.5

A B S M A C H N OR P123z56i89

R P123i567e9

IN0.3650 . 3 8 50 . 3 8 70 . 4 0 30 . 4 0 80 . 4 0 50 . 4 0 10 . 3 9 70 . 3 8 9PER C EN T

S P A N5 .0 01 0 . 0 015.-003 0 . 0 05 0 . 0 07 0 . 0 08 5 . 0 09 0 . 0 09 5 . 0 0

O U T0. 46 40 . 4 7 70 . 4 8 00 . 4 8 80 . 4 9 50 . 5 0 60 . 5 1 S0.5-160 . 5 2 2

IN- 0 . 0- 0 . 0- o . o -- 0 . 0- 0 . 0- 0 . 0- 0 . 0- 0 . 0- 0 . 0R ELIN2 6 5 . 02 6 0 . 42 5 4 . 32 3 7 . 22 1 4 . 0192.71 7 7 .9172.7166.5

O I J T3 . r3 2 . 53 2 . 73 5 . 43 8 . 84 0 . 24 2 . 14 2 . 44 3 . 1V E LO ' J T186.71 9 2 . 41 8 7 .3167.51 4 4 . 91 3 4 . 4129.8129.2129.9

R E L M A C H N O "IN0.7 8 80 .7 7 60 . 7 5 80 . 7 0 90 . 6 4 00 . 5 7 60 . 5 3 10 . 5 1 60. 49 7

I N C I D E N C EM E A N6.86.97.38.31 0 . 0 '1 1 .512.112.412.7

s s3.13 . 13.43.74.34.95.15.35.6

O U T0 .5 4 00 . 5 5 80 . 5 4 40 .4 8 80 . 4 2 40 .3 9 50 . 3 8 30 .3 8 20 . 3 8 4

D E V7.36.97 . 47.67.88.58.38 . 47 . 4

IN6 2 .4S O . 4 '5 9 . 35 5 . 35 0 . 34 5 . 241 .03 9 . 73 8 . 5

K E R I D!N122.8126. S1 2 9 .51 5 5 . 11 3 6 .61 3 5 . 71 5 4 . 21 3 2 . 91 3 0 . 3M E R I D M AIN0.3650 . 3830 . 3 8 70 . 4 0 30 . 4 0 80 . 4 0 50 . 4 0 10 . 3 9 70 . 3 8 9

D - F A C T0 .4 680 . 4 2 00 .4 2 30 .4 6 20 . 4 9 80 .4 7 50 . 4 3 60 . 4 1 30 . 3 8 0

O U T4 5 . 9- 5 . 84 2 . 15 5 . 5 -2 ^ . 51 2 . 00 . 6- 2 . 3-7.2

!N2G 9 . 72 G 3 . 62 8 G . 42 S 8 . 02 8 3 . 02 3 7 . 92 S 7 . 92 G 7 . 92 3 7 . 9

R A T I Oi;11(1Ij1

V E X T A N GO U T129.51 3 S . 8158.9 '1 3 6 . 31 5 1 . S1 5 ' i . 51 2 9 .81 2 9 . 0128.9C H N OO U T0 . 3 7 5C . 4 C 30 . 4 0 40 . 3 9 7C . 3 3 60 . 3 8G0 . 5 8 30 . 5 6 10 . 5 8 1

EF F0.7980 .8 9 50 . 9 5 00 . 9 4 40 . 9 5 90 . 9 S 9O . S 5 90 . 9 4 30 . 9 3 7

!N- 0 . 0-0. 0- o ! o~ "J . J- 0 . 0

Av J- 0 . 0- 0 . 0- 0 . 0

L O S ST O TC . 1 4 3C . 0 7 50 . 0 4 90 . 0 4 20 . 3 5 50 . 0 2 50 . 0 3 60 . 0 5 10 . 0 5 7

1\i1

. 076.0 7 ! '. 0'9.0 6 5.0 5 9. 05 2 . 0 4 6

. C ' 4 4'.042

VtLO U T 9 4 .6S 3 . 38 9 . 39 6 . 90 6 . 0' . 1 . 01 7 . 11 7 .71 2 0 .6 -

C O E F FP R O F000000000

.1 4 3.0 7 3. O J 9.0 4 2. 0 5 5.0 2 6. 0 3 6. 0 5 1. 0 5 7

IN 1 0 . 1 0V O . 1 ' 41 0 . U1 0 . 1 31 0 . 1 51 0 . 1 41 0 . 1 51 0 . 1 51 C . 1 1

KHEEL!N2 3 4 . 82 2 6 .42 1 8 . 71 9 5 . 01 6 4 .71 5 3 . 81 1 6 . 8' 1 0 . 21 0 3 . 6K E R I DV E L R1 . G 5 81 . 0 8 01 . 0 6 91 . 0 0 90.9650 . 5 6 90 .9 6 70.971.0 . 9 8 9

R A T I O1.2291 . 2 4 11 . 2 4 21 . 2 5 11 . 2 1 11 . 1 8 71 . 1 6 51 . 1 5 11 . 1 4 5

S P E E DO U T228.62 2 1 . 52 1 4 . 91 9 4 . 1166.21 3 9 . 01 1 3 . 41 1 1 . 31 0 4 . 2

P E A K S SM A C H N O1.3151 .2 5 41 . 2 5 11 . 1 1 50 . 9 6 60 . 8 2 70 . 7 2 80 . 6 5 60 . 6 6 4L O S S P A R A MT O T0 . 0 4 90 . 0 2 50 . - 0 1 7o . a u0 . 0 1 10 . 0 0 80 . 0 0 90 . 0 1 20 . 0 1 3

P R O F3 . 0 4 90 . 0 2 50 . 0 1 70 . 0 1 40 . 0 1 10 . 0 0 80 . 0 0 90 . 0 1 20 . 0 1 3

3 4


38/109

TABLE VH. - Continued,(k) 80 Percent of design speed; reading 3006

R A D I IR P1234567e9

R?I234568\4

IN2 - 5 . -1222 3 . 5 5 92 2 . 7 3 820.28-117.1701 4.23212.1"11. -17310 . 813

A B S:N1 0 ? . 1 1 5 . 21 1 6 . 4i".1 3 5 . ;:25.212 3 . 612 3 . 212' .i

O U T23.7822 3 . 0 6 322.3-172 0 . 19517. 32 81 4 . 4 6 01 2 . 3 1 11 1 . 5 9 310 . 876

V E LC U T1 5 4 . 1156 . 51 6 0 . 6162 . 8165 . 3!66 . 81 7 0 . 6170 . 51 - 3 . 4

A B S M A C H N ORP\23i,567e9

R P23i.56789

iN0 . 32 40 . 3 4 20 . 3 4 50 . 5 6 4

0 . 5 7 53 . 5 7 30 . 3 S 90 . 5 S 70 . 5 6 2

PERCENTSPAN5 . 0 01 0 . 0 0! 5 . 0 03 0 . 0 05 0 . 0 07 0 . 0 00 5 . 0 09 3 . 0 09 5 . 0 0

O U T0.4420 . 4 5 20 . 4 5 50 . 4 730 . 4 830 . 4 8 S0 . 5 0 50 . 5 0 30 . 5 1 2

A B SIN- 0 . 00 . 00 . 0- 0 . 0- 0 . 00 . 00 .0.- 0 . 0

R ELIN2 5 8 . 22 5 5 . 82 4 7. 72 5 0 . 02 0 5 . 7185 . 51 7 0 . 1165 . 4159 . 7

B E T A MO U T48.5 9.3 7.3 8 .41 .41.43.43.44.

V E LO U T152.91 7 0 . 51 7 3 . 81 5 7 . 91 3 6 . 212 7. 212 4 . 212 5 . 512 5 . 7

192458380

R E L M A C H N OIN0 . 7660 . 7 5 40 . 7 5 60 .60 50 . 6 1 60 . 5 5 20 . 5 0 70 . 4 950 . 4 76

I N C I D E N C EM E A N9. 49.51 0 . 01 0 . 91 2 . 51 5 . 81 4 . 414 . 51 4 . 8

s s5.75.76 . 06.56.87 . 17.47.47.5

O U T0 . 4 3 90 .4 920 . 5 0 30 . 4 590 . 5 9 80 : 5730 . 3 6 60 . 3 6 40 . 5 7 1

D E V9.16.37.98 . 17.89 . 08.58 . 17 . 3

RELIN6 5 . 06 3 . 06 2 . 05 7 . 95 2 . 84 7 . 54 3 . 34 1 . 84 0 . 5

M E R I DIN1 0 9 . !1 1 5 . 2 1 1 6 . 4122.2125. i12 5 . 21 2 5 . 812 3 . 21 2 1 . 4

B E T A MO U T4 7 . 84 5 . 242.65 5 . 02 4 . 612.50 . 6- 5 . 1-7 -. 4

V E LO U T1 0 2 . 81 2 0 . 21 2 7 . 812 7. 71 2 5 . 9124.2i24.21 2 3 . 21 2 4 . 7

T O T A L T E M PIN2 2 8 . 72 8 3 . 52 2 8 . 42 8 8 . 02 S 8 . 02 87. 92 8 7 . 92 3 7 . 92 87. 9T A N G.IN- 0 . 00 . 00 . 0- 0 . 0

- O . C0 . 00 .0 .- 0 . 0

R A T I O1 . 0 8 7. 0 79. 0 74. 0 68. 0 6 1. 0 52. 0 4 7. 0 4 4. 0 4 3

V E L 'O U T1 14. -71 0 0 . 397. 21 0 1 . . 11 0 9 . 41 1 1 . 21 1 7 . 01 1 8 . 1120.5

M E R ! D M A . C H N OiN0 . 3 2 40 . 3 4 20 . 3 4 60 . 3 6 40 . 3 7 30 . 3 7 30 . 3 6 90 . 3 6 70 . 3 6 2D - F A C T0 . 62 20 . 5 1 40 . 4 7 70 . 4 5 50 . 5 2 80 . 4 9 00 . 4 4 30 . 4 2 30 . 3 8 0

C U T0 . 2 950 . 3 4 7C . 3 7 00 . 3 7 10 . 5 S 20 . 3 6 50 . 3S60 . 3 S 50 . 3 S 3

EF F0 . 6 5 90 . 7 o 7C . S 550 . 8250 . 9240 . 9540 . 94 60 . 9 3 90 . 9 5 2

L O S S C C Z F FT O T0 . 2 3 3o . i & :0 . 1 2 70 . 0 5 5G . C S 70 . 0 4 20 . 0 5 50 . 0590 . 0 6 7

P R O F0 . 2 850 . 1 9 10 . 1 2 70 . 0 9 5O . G S 70 . 0 4 2O . C 5 50 . 0590 . 0 6 7

T O T A L PRESSIN1 0 ; 1 11 0 . 1 41 0 . 1 31 0 . 1 41 0 . 1 41 0 . 1 51 0 . 1 51 0 . 1 31 0 . 1 2

XHEELIN2 3 4 . 12 2 6. 12 1 3 . 61 9 4 . 8164 . 6! 3 6 ; 61 1 6 . 61 1 0 . 31 0 3 . 7H E R IDV E L R0 . 9 4 21. 0 4 31 . 0 9 81 . 0 4 50 . 9 9 00 . 9921 . 0 0 3; . o o o1 . 0 2 7

R A T I O1 . 2 1 7.224. 2 54.227. 2 1 0. 185. 165

1 . 1 5 21 . 1 4 6

S P E E DO U T2 2 7 . 92 2 1 . 52' .4 .91 9 4 . 01 6 6 . 11 3 8 . 81 1 8 . 21 1 1 . 51 0 4 . 4

P E A K S SM A C H N O1. 34 61.295.1.2621 . 1 3 80 . 9 8 10 . 8 5 50 . 7 5 40 . 7 0 30 . 6 6 9

L O S S P A R A MT O T0 . 0 9 50 . 0 640 . 0 4 50 . 0 5 20 . 0220 . 0 1 20 . 0 1 50 . 0 1 40 . 0 1 5

P R O F0 . 0 9 30 . 0640 . 0 4 30 . 0 5 2: 0 . 0 2 20 . 0 1 20 . 0 1 30 . 0 1 40 . 0 1 5

3 5


39/109

T A B L E VII. - Continued.(t) 90 Percent of design speed; reading 3016

R A D I IR P123456" f89

R?123456765

I N24.42223.56922.75820.2341 7 . 1 7 0U.232t 2 . u a11.4731 0 . 8 1 3

A S SI N183.5193.3194.2203. 72D6.6204.3232.1200.9195.9

O U T25.78223. 5322.5472 0 . 1 0 617.3281 4 . 4 6 01 2 . 3 1 111.5931 0 . 8 7 6

V E L 'C U T205.4207.2207.721 4.7220.8224.8231 .7232.2227.6A 3 S M A C H N ORP

I23456789

RPI23456789

I N0.5550.5870.5900.6210.63!0.6240.6170.6130.600

P E R C E N TSPAN5.001 0 . 0 015.0030.0050.0070.0085.0090.0095.00

OU T0.6040.6100.6120.6350.6550.6700.6940.6960.682

A S S: N0.0 . 10 . 10.0.0.c .0.0.R E L!N

321.'319.6312.728.7277.4255.6240. S235.9228.9

B E T A XC U T22.322.022.425.629.952.254.335.035.9

V E LO U T260.9257.7251.2230.5206.4195.71 9 1 . 41 90.5185.0

R E L M A C H N OI N0.9710.9700.9500 . 9 1 10.8480.7800.7350.7200.697

I N C I D E N C EM E A N-0.5-0.8-0.40 . 01 . 53.24.14.34.9

SS-4.2-4.6-4.3-4.6-4.2-3.4-3.0-2.8-2.2

O U T0.7670.7580.7400.6820.6130.5770.5730.5710.555

D E V

*ELi N -55.:5 2 . e5 1 . 647.04! .936.952.931.630.7

K E R I DI N183.51 93.3',94.2205.7205.6204.3202.1200.9196.9

B E T A : - ;O U T45.24 1 . 84 0 . i52.92 1 . 91 0 . 90 . 7-2.4-5.0

V E LO U T1 9 0 . 0192. i192.0193.71 9 1 . 51 90.31 9 1 . 41 9 0 . 5184.3

T O T A L T E M ?Z'22f.282 326

I N-". ft

o'.Od . o^i '

' .237.72320267.77.67.7

T A NI N0.2C . 20.20.20.20.20.20.20.2

R A T I O1 .069i . 0 6 91 . 0 6 Gi . 0 6 81 . 5 5 51 . 0 6 11 .0571 . 0 5 51 . 0 5 2

G V E LO U T78.177.579.192.7

109.91 1 9 . 7130.61 33.0133.5

M E R I D M A C H N OI N0.5550.5870.5900.6210.6310.6240.6170.6130.600

D - F A C T

OUT0.559-0.5550.5660.5730.5680.5670.5730.57!0.553E F F LOSS C O E F FT O T4.64.9

5.44.95.27.48.48.89.7

0.3050.3070 : 3 1 10.3560.3950.5800.3410.3260.321

0.9270.9320.9951.0051 .0030.9700.9660.9460.870

0.0.0.-0.-0.0.0.0.0.

0360090020030020 1 902!034080

PROF.0.0240.002-0.002-0.003-0.0020.01 90.02!0.0340.080

T O T A L PRESSI N1 0 . 0 31 0 . 1 31 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 41 0 . 1 410 .1. 0 :

WHEELI N263.7254.7245.3218.7185. 3153.81 3 1 . 1125.91 1 6 . 9K E R i DV E L R1.0360.9940.9890.95!0.9270.9310.9470.9470.936

R A T I O1.2441.2571.2591.2601.2491.223!.2081 .1 941 . 1 6 7

S P E E DO U T256.8249.22 4 1 . 1217.8187.0156.3132.91 2 5 . 11 1 7.6

P E A K SSM A C H N O1.3791.5271.2931 . 1 7 21.0240.8750.7430.7200.697

LOSS P A R A MT O T0 . 0 1 30.0050 . 0 0 1-0.00!- 0 . 0 0 10.0050.0050.0060 . 0 1 8

PROF0.0090 . 0 0 1- 0 . 0 0 1- C . 0 0 1-0.00!0.0050.0050.0080.01 8

3 6


40/109

TABLE VH. - Continued,(m ) 90 Percent of design speed; reading 2997

R A D ! !RP123456/89

R ?*

2345D~e

I N24.42223.56922.73820.28


41/109

T A BL E VH. - Continued,(n) 90 Percent of design speed; reading 2998

R A D I IRP!23456-^89

R P*2345c*"&rf

IN '24. 4222 5 . 5 S 92 2 . 7 5 82 0 .2 841 7 . 1 7 014.23212. 144. \ \ .47 31 0 . 8 1 3

A B SIN6 1 . 369 .770 . 977.88 0 . 07 8 . !7 5 . 7-e .1-' J . w7! .7

O U T23 . 7 8 22 5 . 0 5 32 2 . 3 ^ 72 0 . 1 9 617. 32 81 4 . 4 6 01 2 . 3 1 11 1 . 5 9 31 0 . 8 7 6V E LO U Tl ? 3 . 71 9 7 . 7' 9 6 . 52 0 0 . 12 0 0 . 5" 2 0 4 . 925 9 . C2 3 7 . 22 0 7 . 4

A B S M A C H N OR ?!2345e7e9

R P123456789

;N0.4840 . 5 1 !0 . 5 1 50 . 5 3 70 . 5 4 50 . 5 3 90 . 5 3 !0 . 5 2 90 . 5 1 8

P E R C E N TS P A N5 . 0 01 0 . 0 015.-003 0 . 0 05 0 . 0 07 0 . 0 08 5 . 0 09 0. 009 5 . 0 0

O U T0 . 5 6 20. 5 7 50 . 5 7 20 . 5 8

nasa stage 53 design report

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