m emoran dum - unt digital library/67531/metadc52845/m...u divergence angle, deg p boattail angle,...
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R ESEARCH M EMORAN DUM
OFF-DESIGN PERFORMANCE OF DIVERGENT EJECTORS
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By Milton A. Beheim
Lewis Flight Propulsion Laboratory Cleveland, Ohio
C ~ D o C u ? . m r n
This materlal contains information affecting th, Nntional Defense of tbe United States within tbe meaning of the e s p i o ~ g ~ lawa, TYtls 18, U.S.C., Sea. 793 and W, tbe trpIyImk38ion or revelation of which in my manner to an unauthoriced p s o n is pmhtblted by law.
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
WASHINGTON September 30, 1958
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RESEARCH MJ3MORANwM
OFF-DEIGN PERFORMANCE OF DrVERGENT EJECPORS*
By Milton A. Beheim
SUMMARY
The off-design performance of fixed- and of variable-gemetry di- vergent e jectors was investigated. The ejectors, which were designed f o r turbojet operation a t Mach 3, were investigated i n the Mach number range 0.8 t o 2. The performance of a fixed-geometry ejector with high secondary-flow ra t e s was competitive w i t h t ha t of more complex variable- geometry ejectors. Variable-geometry ejectors with compromises t o re- duce mechanical complexity produced performance reasonably close t o that of an idea l variable ejector.
INTRODUCTION
Simple fixed-geometry divergent ejectors designed f o r good perform- ance a t high f l ight speeds (e.g., Mach 3) suf fer large performance losses a t low speeds. on the geometry and the j e t and stream interaction. that the performance of such an ejector c m be so poor a t low speeds that an airplane would not be able t o accelerate t o the high design speed. In other cases where suf f ic ien t thrust w a s available during acceleration, excessive fue l consumption occurred.
This loss resu l t s f r o m j e t overexpansion, which depends Analyses have shown
The following techniques of solving the problem a re considered i n t h i s investigation: off-design performance; (2) employ variable geometry; (3) employ large amounts of secondary airflow t o f i l l i n the excess area of the exit. These schemes were investigated i n the NACA L e w i s 8- by 6-foot tunnel i n the Mach number range 0.8 t o 2.
(1) Compromise the design performance t o improve
SYMBOLS
CD
D b o a t t a i l plus base drag
b o a t t a i l drag coefficient based on maximum cross-sectional area
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maximum forebody diameter
primary-nozzle diameter
spoiler diameter
secondary-nozzle diameter
ejector gross thrust
gross thrust of ideal completely expanded primary flow
axial distance from primary-nozzle exit to ejector exit
Mach number
bypass mass-flow rate
secondary mass-flow rate
maximum capture mass-flow rate of inlet
primary total pressure
secondary total pressure
free-stream total pressure (upstream of model)
local Pitot pressure
base static pressure
boattail static pressure
exit-plane static pressure
free-stream static pressure (upstream of model)
primary total taperatwe
secondary total temperature
free-stream velocity
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3
Ejector Models
Thirteen different e jectors were used i n this investigation, each ident i f ied by number. i, and each sketch i s accompanied with a table of the geometrical param- eters. 1 2 were mounted on the cyl indrical section of the model, which had an 8-inch outside diameter. With ejector 13 the outside diameter of the cylinder was reduced from 8 t o 6.4 inches by an abrupt step 22 inches upstream of the e x i t plane.
Sketches of the ejectors are presented i n figure
Ejectors 1 t o These parameters are a l s o summarized i n tab le I.
Ejectors 1 t o 9 and 13 had low boat ta i l angles representative of nacelle-type instal la t ions. as with cer ta in fuselage-type installations.
Ejectors 10 t o 1 2 had high boa t t a i l angles
Ejectors 1 t o 9 were investigated with e i ther of two primary- nozzle-exit diameters corresponding t o operation with f u l l afterburning and with no afterburning. "he r a t i o of nonafterbuming t o afterburning primary-nozzle diameter was 0.75.
Ejectors 1 t o 6 ( f igs . l (a ) t o (d)) were fixed-geometry types with various values of the geometrical parameters t h a t a f f ec t e jector per- formance (such as expansion rat io , secondary diameter ra t io , divergence angle, etc.). Ejector 3 had a divergent wall contoured (by the method of re f . 1) t o produce nearly axial flow a t the ex i t plane.
A l l e jectors except ejector 3 were conical.
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4
T w ~ M ~ d i f l p ? t $ P o n b ~ f y j e c t p ~ + ~ t miproye ?;y$es$gn performance a r e sho& fi Tlg& ,fer. : Tk#Zg w e iJ):spotler r-q $0 pcourage j e t separatio"; Ai?? (7 air'ih';fectfbn %fkbugh Mfrfulbf. sloes ih the divergent w a l l t o encourage j e t separation and t o fill i n excess flow area a t the ex i t plane. simultaneously.
These techniques were investigated independently and a l so
One type of variable-geometry ejector (7) that was investigated i s i l l u s t r a t ed i n figure l(f). The divergent portion was assumed t o be com- posed of several leaves that could be rotated i n such a manner as t o vary the e x i t area while maintaining a f ixed secondary diameter. Mach number (and simultaneously nozzle pressure r a t io ) decreased, the exit area would be decreased t o provide the correct e x p s i o n ra t io . The two- step boa t t a i l geometry that i s shown would r e su l t i n bigher b o a t t a i l drag a t Mach 3 than would occur i f a single boa t t a i l angle had been selected, but it would incur l e s s drag with low-speed positions. ejector of t h i s type w a s not constructed; but ra ther various posit ions of the movable portion corresponding t o operation a t various Mach numbers were selected, and models were constructed t o simulate these conditions.
A s f l ight
An ac tua l variable
Another variable-geometry ejector (8) that was investigated i s shown i n figure l ( g ) . be constructed of leaves that could be rotated t o vary e x i t area while maintaining a constant secondary diameter. However, i n this case the boa t ta i l was kept fixed. A s a resu l t , as e x i t area decreased, base area increased. The model was designed with a removable base p la te t o invest i - gate the e f fec t of base bleed flow. Again, fixed-geometry models were constructed t o simulate various positions of i n t e re s t of the movable por- t ion of the ejector.
A s with e jec tor 7, the divergent portion was assumed t o
A t h i r d ty-pe of variable-geometry ejector (9) that was investigated i s shown i n figure l ( h ) . both fixed and tne secondary diameter was variable. was assumed t o be constructed of leaves that were hinged a t the e x i t plane. A t the design Mach number the secondary diameter would be a t i t s minimum value and would be large enough t o permit the passage of the cooling secondary airflow. eter would be increased t o permit the flow of suf f ic ien t ly large quantit ies of secondary a i r t o f i l l i n the excess flow area a t the e x i t plane and prevent overexpansion of the primary flow. As with the other variable ejectors, fixed-geometry models simulated posit ions of i n t e r e s t of the hypothetical variable ejector.
In t h i s case the boa t t a i l and ex i t area were The divergent w a l l
A t lower than design Mach numbers the secondary diam-
A s indicated ear l ie r , e jectors 10 t o 12 ( f igs . l(i) and ( j ) ) had higher boa t t a i l angles than those discussed thus far. They simulated a f a m i l y of fixed-geometry ejectors with various values of the geometrical parameters. afterburning) was investigated with these models.
only one primary-nozzle position tcorresponding t o f u l l
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5
Tunnel Instal la t ion
A schematic sketch of the ins ta l la t ion of the model i n the tunnel i s shown i n f igure 2. The downstream portion of the walls of the 8- by 6-foot t e s t section have been perforated t o permit operation a t any Mach number from 0.6 t o 2.1. a t t a i n a more continuous blockage area dis t r ibut ion f o r more uniform flow a t transonic speeds. Primary and secondary air were ducted separately t o the model through the support s t ru t s .
The support s t ru t s were swept forward 4 5 O t o
P i t o t pressure prof i les normal t o the body j u s t upstream of the boat- t a i l a re shown i n f igure 3 f o r several tunnel Mach numbers. were placed i n the plane of the s t r u t and also normal t o it. location is indicated in f igure 2. profiles, it appears that boundary-layer thickness was about 0.8 inch a t Mach numbers 2, 1, and 0.8, and about 1.3 inches a t Mach 1.35.
Survey rakes Their axial
Ignoring unusual dis tor t ions of thy
Local Mach numbers (denoted by Mz) computed by means of the Fbyleigh equation fram the loca l body s t a t i c pressure and the P i to t pressure far- thes t from the body a r e shown i n figure 3. These Mach numbers show a circumferential var ia t ion that probably was due t o the wake from the support s t r u t . A t tunnel Mach numbers 2, 1, and 0.8, the loca l Mach number was lower i n the region behind the s t r u t , and a t Mach 1.35 it was lower i n the plane normal t o the s t ru t . The reason f o r this shift of the low Mach number region as tunnel Mach number is varied is not apparent.
Boat ta i l static-pressure distributions a l so indicated a varying de- gree of circumferential variation. This variation w a s greater a t higher tunnel Mach numbers (e.g., Mach 1.35 compared with Mach 0.8) and a l so generally with higher boa t t a i l angles. The worst condition investigated (ejector 5 o r 6) i s shown i n figure 4 a t several tunnel Mach numbers. The boa t t a i l angle i n this case was 7.5O. The region of lowest pressure was behind the s t r u t a t Mach 1.35, but at Mach 1 it was i n the plane normal t o the s t r u t . A t Mach 0.8 the pressures were fairly uniform, e jectors 10 t o 1 2 had higher over-all boa t t a i l angles (in two s teps) than ejector 5, the pressures were more uniform. The pressures of other ejec- t o r s w i t h lower-angle single-step boat ta i ls were a l so more uniform.
Although
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All ejectors were investigated a t several Mach numbers. With ejectors 1 t o 1 2 several values of primary-nozzle pressure r a t i o were employed a t each Mach number, and with each pressure r a t i o several values of secondary flow were investigated. several values of secondary flow was investigated a t each Mach number with e jec tor 13.
Only one primary-nozzle pressure r a t i o w i t h
For e jectors 1 t o 9 f u l l afterburning was assumed f o r Mach numbers 1.35 and greater, and no afterburning f o r Mach numbers 1.35 and less . The assumption of the Mach number a t which afterburning was turned on did not a f f e c t the generali ty of the conclusions. For e jectors 10 t o 13 f u l l afterburning was assumed t o occur over the Mach number range of the in- vestigation. about 80° F.
Total temperature of both primary and secondary a i r was
Data Reduction
Weight-flow ra t e s were obtained with standard ASME or i f ices . mary t o t a l pressure was cmputed from the primary weight-flow r a t e and measured s t a t i c pressures i n the primary nozzle upstream of the con- vergent- portion. Secondary t o t a l pressure w a s measured with rakes up- stream of the primary-nozzle-exit station.
Pr i -
Because the force-measurement apparatus did not perform with con- s i s t en t accuracy during the test, ejector gross thrus t (exit-plane t o t a l momentum) w a s generally computed from the sum of the t o t a l mamentum of the primary and secondary streams a t reference s ta t ions within the ejector plus the sum of w a l l forces i n the axial direct ion between the reference s ta t ions and the e x i t plane. In general, this procedure gave sa t i s fac tory resu l t s . Ekceptions occurred when large quant i t ies of secondary airflow were used (specifically, the exceptions were ejector 8, Mach 1.35 with no afterburning, and e jec tor 9, bkch numbers 1.35 and 1.0 with no afterburn- ing) . ceeded the maximum theoret ical value with the given secondary and primary weight-flow rates and t o t a l pressures. i n f igure 5 f o r e jector 8. of adjusted th rus t r a t i o (computed frm the gross th rus t obtained by the procedure described) exceeded the maximum possible value a t very high values of secondary-flow ra t io . This did not occur a t Mach 1.0 ( f ig . 5(b) ) , which was the more typical situation. It i s believed tha t t h i s e r ror was a r e s u l t of circumferential variations of the secondary flow that were not detected with the instrmeotat ion employed and that became
In these cases the thrus t computed by th i s procedure s l i gh t ly ex-
This discrepancy i s i l l u s t r a t e d A t Mach 1.35 (f ig . 5(a)) the measured value
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important only when the secondary-flow ra te was unusually large. For these exceptional cases, the maximum theoret ical values were used i n the A.NALYSIS section.
With the modified versions of e jector 1 (i.e., with spoi lers and with air inject ionj the waii surfaces were too irrzg-Llar t o e v s l i ~ t e the v a ~ force. s t r a i n gage and bellows arrangement) were used of necessity. configurations the apparatus appeared t o be operating reasonably well.
Therefore, the data from the force-measurement apparatus (a For these
Thrust Ratio
In the ANALYSIS section of the report an effect ive thrus t r a t i o (F - msVg - D)/Fi th rus t r a t i o F/Fi and the boa t t a i l plus base drag D. A t some Mach numbers where these data were not obtained, an estimated value f o r small secondary-flow r a t i o was computed by the following procedure: (1) If the expansion r a t i o was correct for the particular nozzle pressure r a t i o ( fu l ly expanded), a 2-percent l o s s i n gross-thrust r a t i o was assumed t o account f o r f r i c t i o n losses i n the nozzle. gross-thrust r a t i o due t o flow divergence a t the exit plane were computed assuming F/Fi = (1 + cos a)/2. (3) If the primary flow was underex- panded, the addi t ional loss i n gross-thrust r a t i o was computed from a calculation of exit-plane momentum. expanded, estimates of gross-thrust r a t i o were made based on e a r l i e r un- published data. (6) The configurations f o r which these estimates were made did not have bases; therefore, base drag was not needed.
i s evaluated t h a t required a knowledge of the gross-
( 2 ) Additional losses i n
(4) If the primary flow was over-
(5) B o a t t a i l drag was computed from reference 2.
The basic data a re presented i n figures 6 t o 22, Parameters pre- sented a r e thrus t ra t io , e jector pressure rat io , b o a t t a i l drag coeff i - cient, and e i the r base pressure r a t i o ( i f a base existed) or e x i t static-pressure r a t i o as functions of secondary-flow ra t io . static-pressure r a t i o i s useful as an indication whether or not the p r i - mary flow i s overexpanded.
The exit
ANALYSIS
The data of figures 6 t o 22 have been used i n an analysis of the performance of the ejectors over a Mach number range t o obtain a compar- ison of the solutions considered for the off-design e jec tor problem. A s a basis f o r canparison, nozzle pressure-ratio schedules with Mach number were assumed as shown i n figure 23. Two schedules were used: the
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currently or planned f o r the near future, and the schedule f o r e jector 13 is f o r an advanced, hypothetical, low-pressure-ratio turbojet using a transonic compressor with a design Mach number of 4.
The performnce parameter upon which the analysis i s based i s an effective thrust r a t i o (F - msVO - D)/Fi, defined as the ejector gross t h r u s t minus the free-stream momentum of secondary air minus the drag of the b o a t t a i l and base (if there i s one) divided by gross thrus t of the ideal fully expanded primary flow. W i t h this parameter, configurations designed f o r a given engine and nacelle s i ze but having d i f fe ren t a f t e r - body geometries and secondary flows can be compared direct ly .
Fixed Geometry and Low Secondary Flow
If a fixed-geometry e jec tor i s designed t o provide peak performance at a par t icu lar design Mach number, and i f off-design performance i s not a consideration, then the ejector of necessity must have the correct expansion r a t i o f o r that Mach number, and the flow divergence a t the exit plane must be small. Ejectors 1 t o 3 a r e of this type with a design Mach number of 3. Assuming that a 2-percent secondary-flow r a t i o is sufficient f o r cooling purposes over the Mach number range 0.8 t o 3, the performance of these ejectors i n t h i s Mach number range i s shown i n f ig- ure 24. speed range with no afterburning operation. Ejector 2, which had a larger secondary diameter than e jec tor 1, showed b e t t e r j e t separation character is t ics than ejector 1 only a t h c h 0.8. ejector 3 with a contoured divergent wall was about the same as t h a t of the conical ejectors.
Performance of a l l three ejectors was very poor i n the transonic
The performance of
The off-design performance of these fixed-geometry ejectors can be improved, a t the expense of on-design performance, i f the divergence angle i s increased or if the expansion r a t i o i s decreased. A higher divergence angle would improve the j e t separation charac te r i s t ics and thus reduce the degree of j e t overexpansion (although the pressures i n the separated region may s t i l l be lower than i s desirable because of the base-pressure phenomenon (ref. 3) ),. With a smaller expansibn ra t io , the f low would not be as badly overexpanded a t off-design conditions.
With ejector 4 the expansion r a t i o was the correct value f o r Mach 3 operation, as with e jector 1, but the divergence angle was increased from 9' t o 25O. The performance of this e jec tor i s compared with that of ejector 1 i n f igure 25, again f o r a flow r a t i o of 0.02. number afterburning performance of e jector 4 was estimated t o be somewhat less than that of e jec tor 1 because of the higher divergence angle, but large improvements i n performance occurred a t Mach numbers 0.8 and 1.0. However, no improvement was a t ta ined a t Mach 1.35 with no afterburning. the afterburning had been continued t o some lower Mach number than Mach
The high Mach
If
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With ejectors 5 and 6 the expansion r a t io i s decreased t o that cor- With 2-percent flow r a t i o responding t o complete expansion a t Mach 2.2.
the performances of ejectors 5 and 6 were ident ica l and a r e a l s o com- pared h3th tkt ~f e;ezt=r 1 i n figlze 25. underexpansion losses were appreciable (near Mach 3), e jector 5 o r 6 provided higher performance than e i the r ejector 1 or 4. The l o s s i n pe r fomnee of the compromised ejectors (4 t o 6) wits about the same a t Mach 3, but e jectors 5 and 6 were superior at a l l other Mach numbers. Therefore, it appears that a decreased expansion r a t i o i s a much b e t t e r compromise than an increased divergence angle.
Except f o r the reginn where
Fixed Geometry and High Secondary Flow
The reason a fixed-geometry ejector performs poorly a t Mach numbers l e s s than design i s that the e x i t area i s too large f o r the available pressure ra t io . If the secondary flow were increased suf f ic ien t ly a t t h i s condition, it would f i l l i n the excess e x i t area and prevent over- expansion of the primary flow. In designing a fixed-geometry e jec tor that will employ th i s technique t o improve the off-design performance, it i s necessary t o select a proper value of secondary diameter t o opti- mize over-all performance. It i s desirable that there be suf f ic ien t secondary flow t o prevent primary-flow overexpansion and a l so that the secondary flow have as high a t o t a l pressure as possible s o that over- a l l performance will be high. If the secondary diameter i s too large f o r the amount of secondary flow being used, then th ro t t l i ng losses of the secondary air would occur, with an accompanying loss i n e jec tor per- formance. On the other hand, if the secondary diameter i s too small, it may be impossible t o pass suf f ic ien t a i r a t the available pressure.
"he ef fec t of increased secondary f l o w on off-design ejector per- formance i s shown i n figure 26 f o r ejectors 3 and 6 and f o r two posi- t ions of t h e variable portions of ejector 9. Mach 1.35. mum values fo r the various e x i t diameter ra t ios . The effect ive thrus t r a t i o s increased rapidly as flow r a t i o increased even though f u l l free- stream momentum of the secondary air was charged against the ejector. Thus, large gains would be realized if the drag and w e i g h t of the i n l e t system t h a t provides the additional air can be kept low.
These data were obtained a t The secondary diameter ra t ios were not necessarily the opti-
One method of obtaining this additional air i s the use of auxi l iary in l e t s . Another method that was considered i n detai l is the use of the excess air-handling character is t ics of a fixed-capture-area main i n l e t a t lower than design speeds. Typical of i n l e t s of this type i s the one i l l u s t r a t e d i n the sketch of f igure 27. surface i s varied a t each Mach number so as t o maintain an i n l e t mass- flow r a t i o of 1, and excess air is disposed of through some s o r t of by- pass system (see re f . 4).
With th i s i n l e t the compression
For an assumed engine operating w i t h an i n l e t
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of this type, the schedule of bypass mass-flow r a t i o i s shown i n figure 27. and use it i n the secondary passage of the ejector (assuming an a f t e r - burning primary temperature of 3500' R and a nonafterburning temperature of 1600' R), then maximum available secondary-flow r a t i o would be as shown i n figure 27. t ional total-pressure losses i n ducting the bypass air back t o the ejec- to r , and taking the upper schedule of nozzle pressure r a t i o of f igure 23, the maximum available e jector pressure r a t i o becames that shown a l so i n figure 27. In the analyses that follow, where secondary air i s assumed t o be obtained from the i n l e t bypass, the limits of available weight flow and of available pressure shown i n t h i s f igure w i l l apply. i c a l problems of ducting large quant i t ies of high-pressure a i r around the engine are not considered.
If it were possible t o duct a l l of this bypass a i r around the engine
Estimating i n l e t pressure recovery, assuming addi-
Mechan-
Figure 28 shows the improvement i n performance of e jector 6 when large amounts of secondary air are supplied by the i n l e t bypass. In t h i s case the secondary-flow r a t e (also shown i n the f igure) w a s re- s t r ic ted by the pressure l i m i t . Although the secondary diameter r a t i o selected f o r t h i s e jector was not necessarily the optimum, the -rove- ment in performance was large. compromised version of a Mach 3 ejector (i.e., the expansion r a t i o i s less than idea l a t Mach 3). I3ata a t high secondary-flow ra t e s were not obtained with ejectors that were not compromised (e.g., e jector Z), but the beneficial e f fec ts of high secondary flow would be obtained with these ejectors also.
A s discussed ear l ie r , e jector 6 i s a
The e f f ec t on performance of using spoi lers with ejector 1 i s shown i n figure 29. The spoilers were assumed t o be retracted f o r high-speed afterburning operation and extended f o r transonic nonafterburning oper- ation. A t Mach numbers 0.8 and 1 the spoilers caused j e t separation as they were intended t o do, and hence improved performance re la t ive t o the basic unmodified configuration, but f a i l e d t o do so a t Mach 1.35. Even when the j e t did separate, however, the pressures i n the separated re- gionwere s t i l l less than po because of the base pressure phenomenon described i n reference 3. Thus, performance remained r e l a t ive ly low. Using i n l e t bypass air, air inject ion with the spoi lers eliminated the loss i n performance a t Mach 1.35 as shown i n the figure, but the resu l t - ing performance was no be t te r than that of the basic e jector , At Mach numbers 0.8 and 1 the performance was about the same with air inject ion plus spoilers as with the spoi lers alone. With air inject ion alone ( w i t h the air again supplied by the i n l e t bypass), about t he same im- provement i n performance was at ta ined a t Mach numbers 0.8 and 1 as with the spoilers, but there was no improvement over the basic e jector a t Mach 1.35, The secondary-flow rates again were limited by the pressure available.
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11
Although the leve l of performance was low, a fur ther comparison of the performance of the basic e jector 1 with the performance with a i r in- jection i s presented i n f igure 30. A t Mach 1.35 (f ig . 30(a)) the per- formance of the basic ejector w a s higher a t a given flow r a t i o than that with air injection. Therefore, a t this Mach number it would be be t te r not t o use the air- inject ion slots and t o pass a i l am.ils%le aec~z&~qy
30(b)) s l igh t ly higher performance was obtained a t a given flow r a t i o when air inject ion through the slots was employed. A t Wch 0.8 (f ig . 30(c)), the performance was higher when the s l o t s were employed, even
l air through the secondary passage of the basic ejector. A t Mach 1 (f ig .
I w i t h zero secondary flow, than with the basic ejector. Increasing sec- ondary flow through the s l o t s produced relatively small improvements i n I
performance. open the primary flow did not overexpand internally as much as w i t h the basic ejector.
Wall pressure distributions showed that with the s l o t s
Variable Geometry and Low Secondary Flow
An idealized variable-geometry ejector would have the following features: ra t io , (2) variable secondary diameter t o produce a divergent shroud f o r each e x i t position, (3) variable boa t ta i l angle t o avoid base area as e x i t diameter i s varied, with leaves sufficiently long that boat ta i l drag i s negligible. An ex i t of this type m s not tested, because with the nozzle always on design and with negligible drag the effect ive thrust r a t i o i s known t o be about 0.97.
(1) variable ex i t diameter t o obtain the idea l expansion
A simpler version of this ex i t was investigated and is designated The secondary diameter was kept fixed as e x i t area varied, e jector 7.
and in te rna l and external l ines were varied w i t h a single s e t of leaves that were short , and therefore boa t t a i l drag was not negligible. The schedule of e x i t diameter r a t i o employedis shown i n figure 31. ejector was designed so that the idea l expansion r a t i o was attainable f o r afterburning operation between Mach numbers 1.35 and 3. assumed that during the t ransi t ion from afterburning t o nonafterburning operation a t Mach number 1.35 the ex i t area was not changed. sul ted i n overexpansion a t Mach 1.35 (nonafterburning) . 1 and 0.8, the e x i t diameter was near the ideal value. numbers 1 and 0.8 the exit diameter was less than the secondary diam- e t e r (since the la t ter was kept fixed), with the resu l t that the shroud was convergent rather than divergent. re la t ive ly low thrus t par t icular ly a t low secondary-flow ra t io s and high primary pressure r a t i o s . a t least as large as the secondary diameter and permit overexpansion (as a t Mach 1.35, nonafterburning) o r t o determine some optimum intermediate exit position. that would permit secondary diameter t o vary as the leaves rotated might avoid this problem.
The
It was
This re- A t Wch numbers
However, a t Mach
Such a configuration can have
Alternatives w o u l d be t o keep the e x i t diameter
The selection of a different pivot point of the leaves
................................. . . . . . 0 . 0 . : .aowxbmx@= . .a . a .
a . * a * * a 0 0 . 0
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12
. 0 . . 0 . . ......................... ....................... .......... ........ ...... . e . 0 . . 0 . 0 . . :.go&={ i.0 0 . 0.. $L@ RM E58G10a
The performance of ejector 7 is presentedin figure 32 f o r 2-percent flow ra t io . Also shown f o r reference is the estimated performance of the ideal variable e jector described earlier. Although e jec tor 7 would have <ne ideal expansion r a t i o a t Psach 3, i ts performance w i i i be iess than that of the idea l e jector because of the b o a t t a i l drag. Its r e l a t ive ly low performance a t Mach numbers 1.35 and 1 (nonafterburning) was due t o overexpansion and t o the convergent shroud, respectively.
Another e jector that a l so was mechanically simpler than the i d e a l variable e jector was ejector 8. b e a t t a i l were fixed. this ejector i s shown i n figure 33. a t Mach 3 i n order t o a l lev ia te the off-design problem somewhat . The diameter r a t i o was near the idea l value a t Mach numbers between 2 and 1.35. of the secondary diameter i n order t o avoid the problem of the conver- gent shroud. a t a l l Mach numbers less than that. This resulted in overexpansion f o r nonafterburning operation.
The secondary diameter and a l so the The schedule of e x i t diameter r a t i o employed with
The flow was s l igh t ly underexpanded
For th i s e jector the e x i t diameter was never l e s s than the value
The shroud became cylindrical a t Mach 1.35 and remained so
The performance of e jector 8 with 2-percent flow r a t i o (without base flow) i s presented i n f igure 34. e jec tor i s presented as a reference. A t Mach 3 it i s estimated t h a t the performance of e jector 8 would be less than that of the idea l e jector because the flow i s s l igh t ly underexpanded and because of boattail drag. A t transonic speeds the performance i s lower because of (1) overexpansion, ( 2 ) b o a t t a i l drag, and (3) base drag.
Again the performance of the idea l
Variable Geometry and High Secondary Flow
The improvement in performance of e jec tor 8 by employing large amounts of base flow t o eliminate the base drag i s a l so shown i n f igyre 34. It was assumed that the a i r was provided by the i n l e t bypass. The drop i n performance f o r nonafterburning operation was due pa r t ly t o overexpansion of the primary flow and also t o the total-pressure losses of the secondary flow.
Ejector 9 a l so was simpler than the idea l variable e jector i n t h a t the exit area and the boa t t a i l were fixed. The schedule of secondary &Lameter r a t i o that was employed i s presented i n figure 35. extrapolated data and one-dimensional-flow calculations, these values of diameter r a t i o were selected as those t h a t would match the available bypass flow schedule sa t i s fac tor i ly . The performance of this e jec tc r i s presented i n figure 36. A s described i n the Data Reduction section, the measured values of th rus t r a t i o exceeded the theoret ical ly maximum possible value f o r nonafterburning operation.
By means of
The theoret ical values are
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I
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shown i n f igure 36 where this problem occurred. The performance a t Mach 3 again would be less than that of the ideal e jec tor because of b o a t t a i l drag and because the flow was slightly underexpanded (de/$ = 1.6) . The drop i n performance f o r nonafterburning operation occurred because the secondary t o t a l pressure was less than free-stream t o t a l pressure as a r e s u l t of the losses ass-med i n the m a x i - p r e s s u r e - r a t i o schedule of f igure 27.
C o m p a r i s on
The best performing ejectors of those considered thus far are com- pared i n f igure 37. high secondary flow was within the range of performance encompassed by the more cmplex variable-geometry ejectors. i n the low Mach number range was obtained w i t h e jector 9.
The performance of fixed-geometry e jec tor 6 with
The highest performance
Ejectors with N l Afterburning
q e c t o r s 10 t o 13 were investigated with f u l l afterburning over the en t i r e speed range. The supersonic performance of e jectors 10 t o 1 2 has been obtained i n an ea r l i e r investigation, and the speed range i s ex- tended i n t o the transonic range in the present report. of these ejectors based on the same pressure-ratio schedule as that of the previous ejectors i s shown i n figure 38 f o r 2-percent flow ra t io . Ejector 10, which differed from ejector 11 only i n that it had a smaller secondary diameter, had about the same performance as ejector 11. cause these ejectors had high b o a t t a i l angles representative of some fuselage-type instal la t ions, b o a t t a i l drag was high, and thus the general level of performance was low. (corresponding t o complete expansion at Mach 3) than e jec tors 10 and ll. For a given engine and fuselage size, an increase i n expansion r a t i o would r e su l t i n an increase i n exit area and hence a reduction i n boat- ta i l area. r a t i o a t off-design conditions would a t leas t be partly compensated f o r by the decreased boa t ta i l drag. construction, e jector 1 2 had a smaller primary-nozzle area than ejectors 10 and 11; whereas exit area, fuselage area, and boa t t a i l geometry were ident ical . Hence the data of figure 38 do not show the net e f f e c t of a simple change i n expansion ra t io , but rather show the e f f ec t of Mach number on the performance of various ejector geometries. As with ejec- t o r s 10 and 11, the leve l of performance of e jec tor 1 2 was low because of high b o a t t a i l drag, but additional losses occurred with e jec tor 12 because of the greater degree of overexpansion of the primary flow.
"he performance
Be-
Ejector 1 2 had a higher expansion r a t i o
The increased overexpansion losses w i t h the higher expansion
However, because of details of model
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The effect of secondary flow on the performance of ejectors 10 to 12 at Mach 1 is shown in figure 39. formance occurred as flow ratio increased.
Again, appreciable increases in per-
The effect of secondary flow on the performance of ejector 13 is I
shown in figure 40. that for the previous nozzles (see fig. 23). crease in perfomce as a result of increasing the flow ratio differed with Mach number but was appreciable at all Mach numbers. The greatest improvement occurred at Mach 1.5.
The nozzle-pressure-ratio schedule was lower than The magnitude of the in-
SUMMARY OF RESULTS
The off-design performance of fixed- and variable-geometry divergent ejectors has been investigated. operation at Mach 3 and were investigated in the Mach number range 0.8 to 2. The following results were obtained: I
The ejectors were designed for turbojet
1. Large performance losses occurred at off-design Mach numbers with simple fixed-geometry ejectors designed for peak performance at Mach 3.
2. Compromising design performance by increasing the divergence angle or by decreasing the expansion ratio produced large gains in off- design performance. than an increased divergence angle.
A decreased expansion ratio was a better compromise
3. Increasing the secondary airflow to fill in the excess exit area of fixed-geometry ejectors at off-design conditions produced large gains in performance and made them competitive with fairly complex variable- geometry types.
4. Variable-expansion-ratio ejectors with compromises to reduce I
mechanical complexity produced performance reasonably close to that of an ideal variable ejector.
I
5. An ejector with a fixed exit area and a variable secondary diam- eter with high secondary airflow produced the best performance of the types investigated.
Lewis Flight Propulsion Laboratory National Advisory Committee for Aeronautics
Cleveland, Ohio, July 15, 1958
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1. Clj.ppinger, R. F.: Supersonic Axially Symmetric Nozzles. Rep. No. 794, Ballistic Res. Labs., Aberdeen Proving Ground, Dec. 1951.
Conical Boattails. 2. zaCk, john x. ; yLieoretical &zaa-L-e n4 n + r i h . r + i nna nni4 W n i r e rtra u I u u I ~ Y u " I v I I " W Y U ..I._ ---gs for
NACA TN 2972, 1953.
3. Baughman, L. Eugene, and Kochendorfer, Fred D.: Jet Effects on Base Pressures of Conical Afterbodies at Mach 1.91 and 3.12. E57E06, 1957.
NACA RM
4. Gertsma, L. W., and Beheim, M. A.: Performance at Mach Numbers 3,07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3. NACA RM E58B13, 1958.
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16
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Ejector 2 T de
7
(a) Ejectors 1 and 2: dp,nb/dp,ab = 0.75; dm/dp,ab = 2.0.
L
de/dp,ab = 1.8 ds/dp,ab = 1.05
.- 1.21 '/dp,ab = 2.37
7 vdp,ab 0.875 B = 3.50 a = 23'
5 = 20 ejector ejector
L
de/dp,ab = 1.75 dg ds/dp,ab = 1.05
7 l/dp,ab = 2.37 7
L 0 = 20 dg/dp,ab = 1.78
(b) Ejector 3: dp,nb/dp,ab = 0.75; d,,/dp,ab = 2.0 .
de/dp,ab = 1.45 ds/dp,ab = 1.05 (ejector 5)
= 1.21 (ejector 6) L/dp,ab = 1.26 B = 7.50 a = go (ejector 5,)
- 6.5' (ejector 6)
(d) Ejectors 5 and 6: dp,nb/dp,ab = 0 . 7 5 ; dm/dp,ab = 2.0.
Figure 1. - Ejector geometries.
ejector ejector
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18
. 0 . . 0 . . ......................... ....................... .......... ........ ...... . 0 . 0 .
0 . 0 0 . . . : :*e : :.e NJCAiRM E58GlOa 0 .
(e) Ejector 1 with spoilers and air injection.
C . 0 6 2 5 dp,ab (all Slo t s )
de/dp,ab = 1.8 (at M = 3 )
ds/dp,ab = 1 .05 . l/dp,ab = 1.5 5 , = 7'
. --
6, = -11.5' (at M = 3) 1-1 / ' I a = 14' (at M = 3)
(f) Ejector 7 : dp,nb/dp,ab = 0.75; d,,,/dp,ab = 2.0.
de/dp,ab = 1 . 6 (at ds/dp ,ab = 1.05
B = 6.5'
M = 3 )
l/dp,ab = 1 . 6 9
a = 9.5' (at M = 3) - dJdp,ab = 2.0.
de/dp,ab =
ds/dp ,ab = 1 .OS l/dp,;b = 1 . 6 9
p = 5 a = 9.5O (at M
I- I (h) Ejector 9 : dp,nb/dp,ab= 0.75; dm/dp,ab = 2.0.
Figure 1. - Continued. Ejector geometries.
(at M = 3)
= 3 )
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. . . . . . 0 . 0 .
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= 1.21 (ejector
a = 12.5' (ejector 10) 8.50 (ejector 11)
dB/dp,ab = 1'5
(I) Ejectors 10 and 11: dp,nb/$,ab = 1.0; d,Jdp,ab = 2.5.
I- 1.- (k) Ejector 13: dp,nb/dp,ab = 1.0; d,,,/dp,ab = 1.45.
Figure 1. - Concluded. Ejector geometries.
19
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b rl
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0 . . 0 . 0 .
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......................... . 0 . . 0 . .
.......... ....................... ........ ...... 0 . 0 . . . 21
. e .... NACA RM E58G10a : .e: CbNE’IiI&p~~..~ 0 . 0 . . . .
L1
A (a) Mach number, 2.0.
0 .1 .2 .3 .4 .5 .6 . l .9 1.0 Ratio of Pitot to free-stream total pressure, P1/Po
(b) Mach numher, 1.35
Figure 3. - Pitot pressure profiles upstream of boattail.
................................. . 0 . . . . . . . . . . . . . . . . . 0 . . . . . .... e . 0 . . 0 . ......................... 0 . 0 . . 0 . . ........ . ...... . 0 . . 0 . .
CONFIDENTIAL
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22
.
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0 . * . CONFIDENTIAL
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NACA RM E58G10a COWIDENTIAL I 23
.9(
0
-% 8
.94
.9c
.86
.82
.78
(a) Mach number, 1.35.
F&ure 4. - Boattail static-pressure distribution with 7.5O boattal l angle.
CCINFIDENTIAL
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CrnIDENTIAL NACA RM E58G10a
1.14
0 P :
.98
* 82
.74
.66 0 1 2 3 4
Locatlm
- 0 Aarmal t o strut 0 Behind S t N t
6 I - ~
Stat ion froas beginning of boa t ta i l angle, in.
(b) MBch number, 1.0.
p&ure 4. - Continued. Boattail s t a t i c - p e e u r e diatr lbut lon with 7.S0 boattall angle.
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NACA RM E58G10a
Flow
......................... . 0 . . 0 . . 0 . 0 . 0 . 0 0 . . ........ . . . . . . . . . . . . . . . . ...... 0 . 0 . 0 . . 0 . 0 . . .......... ....................... . .... .
CONFIDENTIAL 25
1,oo
.98
96
* 92
,go
Location Normal t o s t r u t BehM s t r u t
I-
. -- 0 1 2 3 4 5 6 7 8
Station from beginning of b o a t t a i l W e , in.
(c) Mach n-r, 0.8.
Figure 4. - Concluded. Boattail statio-preasure distribution w i t h 7.5O boat ta i l angle.
.......... ....................... 0 . 0 . . . . ..... 0 . 0 . . . . . . . . . . . . . . . . . . ...... 0 . 0 . 0 . 0 . . ........ ......................... . 0 . . 0 . . . . .
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......................... ........ . 0 . . 0 . 0 . 0 . ...... . . . . . . . . . . . . . . . . . ....................... .......... . 0 . . 0 . . . . . 0 . 0 . .... 0 . . 0 . 0 .
26 CONFIDENTIAL NACA RM E58G10a
0
.rl Fr
k
4J m E 5 (a) Mach number, 1.35.
Secondary-flow ratio - ii$ ' wP
(b) Mach number, 1.0.
Figure 5. - Comparison of measured and m a x i m u m thrust ratios for ejector 8 with no afterburninR.
....................... .......... ...... . . . . . . . . . . . . . . . . . . 0 . . 0 . . ......................... . . .... 0 . . 0 . 0 . . 0 . 0 . 0 .
. 0 . 0 . ........ . 0 .
CONFIDENTIAL
![Page 28: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/28.jpg)
NACA FM E58G10a
r- W In ?
.................. . . 0 . . . . . . . . . . . . . 0 . . ....
0.. ............ 0 . . . CrnIDENTIAL
. 0 . . 0 . . ........ . ...... 0 . 0 . . . ...........
27
m
S
m z
w . c m G O 3.
ale - E i 3
0 z
0
- . ? ?
m c
- rl N
A e ”’
9 rl
h e 3
S s .. M
rl c
3 e
0 U Gi
0 z
e -
rl
h 0 0 0 (u .-, (u
’u
CONFIDENTIAL
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......................... .... . 0 . 0 .
. 0 . 0 . 0 . . 0 . . 0 . . 0 . ........ . 0 . 0 . ...... . . . . . . . . . . . . . . . . . ....................... .......... . 0 . .
28 CONFIDENTIAL NACA RM E58G10a
.7
.6
.5
. 4
.3
.2
.3 .6 .6
.2 . 4 . 4
.1 .2 .2
0 0 0
0 .005 .01 d m . . ld ML. 4
r’ f i a a u lddaon 0 v u
u ddc G n
m -. 005 -m5 0
1.2 1.2 1.4 I O
2 a.? a L Q d r t R m m .. 1.0
e o u L- m Q4 * r l w f i
1 .o a m 1 .o
.8 .8 0 .02 .04 .06 0 .02 .04 . 0 6 .08 0 .02 .04 . d
Secondary-flow ratio, - :; E (a) No afterburning; Mach (b) No afterburning; Mach (c) No after-
burning; Mach number, 0.8.
number, 1.35. number, 1.0.
Figure 7. - Performance of ejector 2.
....................... .......... . . 0 . 0 . . . . . . .... . . . . . . . . . . . . . . . . . . . . 0 . 0 . ........ . 0 . 0 . 0 . . 0 . . ......................... ...... .
CONFIDENTIAL
![Page 30: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/30.jpg)
......................... . 0 . . 0 . . 0 . 0 . 0 . 0 . . ........ . . . . . . . . . . . . . . . . . ...... .......... ....................... . .... . 0 . 0 . . 0 . 0 . 0 . .
NACA RM E58G10a 29 CONFIDENTIAL
9 r(
k
f 4 3!
E
.. M d
D
al +J OI
P - D v
.......... ....................... 0 . 0 . 0 . . 0 . 0 . . . . . . . . . . . . . . . . . . ...... 0 . 0 . 0 . a . . ........ ......................... . 0 . . 0 . . ..... . . .
![Page 31: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/31.jpg)
. 0 . . 0 . . ......................... 30
.9
.8
.7
.6
.5
CONFIDENTIAL
.6
.5
.4
.3
.2
NACA RM E58G10a
.9
.7
.6
.5
.9
.8
.7
.5
.6 .3 .5 .6 a
% a .
0
4 m
.2 .4 .5 .4 - 3
.2 .1 . 3 . 4
m a la h o 0 .2 .3 J 0
c) w a
-.2 -.l .1 .2
(11 .04 .02 .04 .04 MU L - ec, d ( u
* d * 4 KIL oa,
2; .02 .01 .02 .02
0 0 0 0
.8 .8 1.1 1.0 I O
2 a,? c ) h 0 KI2a
c ) m m m 010
c) h d X d W k
.6 . 9 .9
4 a*
A .4 .7 '-0 .02 .04- 0 .02 .04 .06-'0 .02 .04 .06'"0 .02 .04
Secondary-flow ratio, 2 (d) No after- burning; Mach number, 0.8.
(a) Afterburning; (b) No afterburning; (c) No afterburning; Mach number, Mach number, 1.35. Mach number, 1.0. 1.35.
Figure 9. - Performance of ejector 4. ....................... .......... ...... . . . . . . . . . . . . . . . . . e * e . 0 . . ......................... . . .... 0 . 0 .
0 . 0 .
. . . . e 0 . 0 . ........ . 0 . 0 .
CONFIDENTIAL
![Page 32: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/32.jpg)
NACA RM E58GlOa
......................... . 0 . . 0 . . 0 . 0 . 0 . 0 . . ........ . . . . . . . . . . . . . . . . ...... 0 . 0 . .e.. 0 . 0 . . .......... ....................... . . . . a .
CONFIDENTIAL 31
Secondary-flow ratlo, 2 P y$
(c) NO afterburning; Mach number, 0.8.
(a) No afterburning; M a c h number, 1.35. (b) NO afterburning; Mach number, 1.0.
Figure 10. - Performance of e j e c t o r 5.
.......... ....................... 0 . 0 . . . . ..... 0 . 0 . . . . . . . . . . . . . . . . . . ...... 0 . 0 . 0 . a . . ........ ......................... . 0 . . 0 . . . . .
CCTNFIDENTIAL
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......................... ........ . 0 . e e . e . 0 . ...... e . . . . . . . . . . . . . . . . . 0 . 0 . .... . e . ....................... .......... . . e . 0 . . . e e . 0 .
32
3 3 3 3
CONFIDENTIAL
9 9
NACA RM E58G10a
i 4
Y)
Y
=?
N.
1
,. - 0
3
Y)
3
L D
?
E r m 5
M
3 E L
P
u c m
z m ..-. Y
CL)
k 0 c, 0 a, n a,
k 0
a,
(d E k 0 k k a, PI
I
r l rl
a, k
d I%
2
2l
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......................... . 0 . . 0 . . 0 . 0 . 0 . . 0 . . . . . . . . . . . . . . . . . . . . . . . . . . . ...... .......... ....................... .... . 0 . 0 . . 0 . 0 . 0 . .
NACA RM E58G10a CONFIDENTIAL 33
d e k
.3 .3 .3 al I l k 0 d ;P,R
e d\
- & . k .2 .2 .2
.02 .02 .03 d l rl d MdS c l l d % C I P
0 0 .01
i.0 1.0
0
2 t a" .8 .9 Q 0 d . + o d + + + m .6 .8
A . 7 . . .- 0 .02 .04 .06 0 .02 .04 .06 0 . 02 .04 .06
Secondary-flow ratio, -
(a) No afterburningj Mach (b) No afterburningj Mach ( c ) No afterburningj Mach number, 1.35. number, 1.0. number, 0.8.
Figure 12. - Performance of ejector 1 with spoilers.
.......... ....................... 0 . 0 . 0 . . 0 . . e . . . . . . . . . . . . . . . . . ...... 0 . 0 . 0 . 0 . . ........ ......................... . 0 . . 0 . . ..... . . .
C r n I D r n I A L
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* a ..a *a . a * * * . *a a * * a * * . . *a a * . * . a a . a a . a . . a a .
a . . .a .a . a * * a . a * . a a . a . a a .a*. a * * a a . a .
a a a . a a. a
a * . . a * a * * **.a a * * . *.a * * a . a * . a. . . * a * .a*. a
34
c -- b?
P i m ? r(
CONFIDENTIAL NACA RM E58G10a
2 I:
a .
c o 3. eF. ha, ale ” E G 4 3 m c
.. ,5?
0 z
0 h -
9
2 r(
e 3
5:
9 .. bo d E
3 e PI
m 0 z
e - -
C
3 ” 0 PI 9
C .A
h m .c U .+ 3 rl
h U 0
c) PI 4
PI 0
4
I 0 4
PI a I
c) 4
PI z 4 a
CONFIDENTIAL
![Page 36: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/36.jpg)
......................... . . . . . . . . . . . . . . . . .......... ..e m e * ..e
. 0 . e .... 0 . 0 . 0 .
0 . . 0 . 0 . .
NACA RM E58G10a CONFIDENTIAL
* *
Y
0
N 0 0
N 9
0
. 0 . . 0 . . ........ . ...... . 0 . 0 . e ...........
9 3
c e 3
.c
c
3 M
C
3 e
e, c
0 0
e
4
m
- -
COWIDENTIAL
35
![Page 37: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/37.jpg)
......................... . 0 . 0 . 0 .
0 . 0 .
. 0 . . 0 . . ........ . 0 . . 0 . 0 .
...... . . . . . . . . . . . . . . . . . ....................... .......... . . .... 0 . .
NACA RM E58G10a 36 CONFIDENTIAL
n ?.
N rl 0
m
(D v) N.
u) 0 M 0 . r l rl I” n
d N 9 9
I
9
-r 0
h 9
N 9 m 0
W 0
D
4 v m
3 0 rl c I h
a 0 0 0 VI
m
....................... .......... . . 0 . 0 . . 0 . 0 . ........ . 0 . 0 . . 0 . . 0 . . ......................... .... . . . . . . . . . . . . . . . . . . . ...... . 0 . 0 . . C O m IDENT IAL
c h v 0
n 8
c
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......................... . 0 . . 0 . . 0 . 0 . 0 . . ........ . . . . . . . . . . . . . . . . ......
0 . 0 . . . . 0 . 0 . . .......... ....................... . 0 . . .... . . NACA RM E58G10a CONFIDENTIAL 37
d 9
N 9
0 9
1s GO.. . a, m m m U Z .r( Gi 0 . m .. 7 4 b o - O C G - Zda, a - E 9 9 2 3 22
8 N 0 0
h 0 h 0 9 r(
9 ? (0
.. '9 0
h e 1
C . O W d . E d ..I . boa z5 h a e
U Gi B
I
v) d
al
k rl a . . 1 .
0 d
m 9
W
9
d 9
N 9
d 0 m N. 9
r?' d
B e 1
... M a 5% 4 "
0 2
a - -
9 9
. . . . . . CONFIDENTIAL
![Page 39: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/39.jpg)
38
. . . . . . . ......................... ...... . . . . . . . . . . . . . . . . . . . . 0 . 0 .
0 . . . ........ . 0 . . . .... . . . . ....................... 0 . 0 . ..........
d 3 3 3
CONFIDENTIAL
3
3
* N 9 9
NACA RM ESBGlOa
3 3
F 0 ci 0 e, .T-J e, L
3 4
C OIWIDENTIAL
![Page 40: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/40.jpg)
em. eemm m e e e m m m m e
em. meme
NACA RM E58G10a C O N F I D E N T I A L
m * 0 9 9
39
.. 03
0
h e 3
i:. O M @In z *
d
M - c a de C\ h m 3- e
m U 4
0 z
m h
v
M LD
d
a
% e
.I
9 rl
h m
1
I: V
z M
C
3
m U 4
0 z
e
e
.. 3
e
h
v
d 4
0 m
m e
s
8
.i
03
U 0 a, -3
m 4
m ” C E
0 4
m D.
e aJ e
d 0
C 0 U
I
W .-I
aJ
2 J 4 a
C O N F I D E N T I A L
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.e 0.0 e,. *e . e... e.. e... .e. . e . e . * * * m.
e e . . . . e *
40
.9
.8
.7
CONFIDENTIAL NACA RM E58G10a
.9
.8
.7
.9
.8
.?
.2 .3 .3 aJ h
ln\ w w h a
2 I%@
a ~ .1 .2 .2 :: .: t'c, V d (uk w '3
0 .1 .1
.03 .09 .04 . - ? I
'2 hoc; Q d k C F1 + h aJ (uv d a O d 0 v u
.02 .07 .02 a
v I O R .6 1.0 1.0 .ri aJ\ 4 k F9 d 3 c 4 Pln m u ] -. w o a, k d (D P42 d .9 m .5
0 .02 .04 0 .02 .04 0 .02 .04 P i n
Secondary-flow ratio, - ws E W P
(a) No afterburning; (b) No afterburning; (c) No afterburningj Mach number, 1.35; Mach number, 1.0; Mach number, 0.8;
de/%, 1.53. de/%, 1.53. de/dp, 1.53.
Figure 17. - Performance of ejector 8 without base flow.
.e 0 e ..e *.*e e 0 e.. ..e 0.. 0 0.. ...e .e.
0 . e. e e. .*e .*e e.. e... e.. ...e .e *
e... e . e . e . e . e . e .e .e . ..e e ..e .
e . e e m e e . e * e 0 . e . . . e . . . e e . . . . 0 .
COKFIDENTIAL
![Page 42: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/42.jpg)
......................... . 0 . . 0 . . 0 . 0 . 0 . . 0 . . ........ . . . . . . . . . . . . . . . . . ...... 0 . 0 . 0 . . . .... . 0 . 0 . . .......... .......................
NACA RM E58G10a CONFIDENTIAL
N d rl
Lo M rl m rf rl 4
....... .......... 0 . . . . 0 . 0 .
............ . .................... . .
rl In
.... ............. . . 0 . 0 . . . 0 . b 0 . . 0 . ...... 0 . ........ 0 .
41
m h
w 0
a v a,
4
a, 0 G
E
CONFIDENTIAL
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. 0 . . 0 . . ........ ...... . . 0 . 0 . . ........... 42
......................... . 0 . 0 0 . 0 . 0 . . . . . . . . . . . . . . . . . .... . 0 . . 0 . 0 . ............ .......... CONFIDENTIAL NACA RM E58G10a
(D
rl
.. 9 rl 9
rl F- a, P
5 m
m
.................................... . -m2?’3s ?TXZ
0 . .... : O . a W O a = :.. . 0 . 0 . . ........ . ...... . . ........ . ......................... 0 . 0 . 0 . 0 . . 0 . . 0 . . CONFIDENTIAL
A
ld a
a, VI
M .i C
3 P
a,
4
0 z
a - v
dt m r-
a < a
ln
rl
h P
3
r:
x
bo
d C
P al * Q
0 z
..I
r
s ..
5
0 v
F- 4 2 0 u c) a,
h
a, 0 c
E h
a, [4
a a, a rl 0 C
U
I
m rl
a, $4
4 a 27
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......................... . 0 . . 0 . . 0 . 0 . 0 . . . . ........ . . . . . . . . . . . . . . . . ...... .......... ....................... . . . . .... 0 . 0 . b 0 . 0 . 0 . 0
NACA RM E58G10a
9 3 3
4 ? W
3 4
4
d 4 m 3
m
CON!?IDENTIAL
c m -? N 0 9 9
W d N 0 9 9
m m d 4 9 4
03
rl 0-
3 30
0
N 3
m 4
d 9
43
COrnIDENTIAL
![Page 45: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/45.jpg)
.................. . 0 . . 0 . ................... . 0 . . 0 . . ........ ...... . 0 . 0 . . . . . . . . . . . . . . .... . 0 . . . .
0.. . . . . 44 CONFIDENTIAL
d N 9 9
dl 0 0
? 9
. . - T .I.I ao 3
....... . 0 . ..... . 0 . ....... NACA RM E58GlOa
0 rl
m 9
ID
9
* 9
@l
9
0 9
rl rl
N 0
rl rl
O d m ‘ O T 3 E . l
m 0
h D 3
F:
P h
0 -
w . c 3
9 w r l c
h a e o P C
3 E C h
c c O h
5 : a .-.I P
0 N
~m
m w
- .
27
a
ua
rl ?
B z s
E
S
5
a - -
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......................... . 0 . . 0 . . 0 . 0 . 0 . . . . ........ . . . . . . . . . . . . . . . . ...... .......... ....................... . . . . .... 0 . 0 . . 0 . 0 . 0 . .
NACA RM E58GlOa C ONF IDENT IAL 45
1.1
1.0
. s
. u
.7
Secondary-flow r a t l o tP i; (b) Mach nunber, 1.0. ( c ) Mach number, 0.8. ( a ) Mach number, 1.35.
Figure 21. - Performance of ejector 12.
0 . ................................. 0 . . . . ..... 0 . 0 . . 0 . . . . . . . . . . . . . . . . . 0 . 0 . . 0 . . ........ . . o . m . . 0 ......................... . 0 . . 0 . . CONFIDENTIAL
![Page 47: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/47.jpg)
......................... . 0 . . 0 . 0 . 0 . . . .... 0 . .
. 0 . . 0 . . ........ . 0 . 0 .
...... . . . . . . . . . . . . . . . . . ....................... .......... 0 . 0 .
46 C OW IDENT IAL NACA RM E58G10a
1. .. 0
I *ti
.o .04 .06 .08 .10 .12 .14 .16 .18
....................... .......... L . - 0 . 0 . . . . . . ...... . 0 . . 0 . 0
. . . . . . . . 0 ......................... b o
CONFIDENTIAL
![Page 48: M EMORAN DUM - UNT Digital Library/67531/metadc52845/m...U divergence angle, deg P boattail angle, deg Subscripts : ab afterburning a local nb no af terburning normal distance from](https://reader033.vdocuments.site/reader033/viewer/2022052007/601c0a0c6af154350b56549a/html5/thumbnails/48.jpg)
NACA RM E58G10a CON? IDENTIAL
9 m
“0. N
u)
cu
N
N
? $ “ 4
‘D. l-i
d: l-i
0 l-i
47
Ei m m
H
1
K) N
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4%
n I
0
8” ,
PI
0 .rl e k
......................... . 0 . . 0 . 0 . 0 . ...... . . . . . . . . . . . . . . . . . .... . 0 . . 0 . 0 . ....................... .......... . 0 . . 0 . . ........ . . 0 . 0 .
CONFIDENTIAL NACA RM E58G10e
Mach number,
Figure 24. - Effect, of flight Msch number on fixed ejector performance. Secondary-flow ratio, 0.02.
F ‘ I
.0 1.0 1.2 1.4 1.6 1.8 2.0 2.2 2.4 2.6 2.8 3.0 Mach number, &&,
Figure 25. - Effect of design compromises with fixed edectors. Secondary-flow ratio, 0.02.
....................... .......... . 0 . 0 . .... . . . . . . . . . . . . . . . . . . e ........ . ......................... 0 . 0 . 0 .
0 . 0 . . e ...... . 0 . . 0 . . . . e . CONFIDENTIAL
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......................... . 0 . . 0 . . 0 . 0 . 0 . . . . . ........ . . . . . . . . . . . . . . . . . ...... 0 . 0 . . . . . .... . 0 . 0 . . .......... .......................
NACA RM E58G10a CONFIDENTIAL
1.0
.8
.7
.6
.5
.5
.4
.3
.2
.1
0
1.40 2.40 1.45 1.60
.1 .2 .3 .4 .5 .6
Secondary-flow ratio, - wP
49
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. . . . . . . ......................... ........ . . . . . . 0 . . . ...... . . . . . . . . . . . . . . . . . . . . . . . .... . . . . . . . . ....................... .......... 50 C 0" IDENT IAL NACA RM E58G10a
- . ....................... .......... . . . . . . . .................... . ...... . . ...... . . . .%-@ . mJ*btKia . . :.. . . 0 . ........ . . . 0 . 0 . . . .
* * c'O&IJ)~,L
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......................... . 0 . . 0 . . 0 . 0 . 0 . . 0 . . ........ . . . . . . . . . . . . . . . . ...... 0 . 0 . . . . . .... 0 . 0 . . .......... ....................... .
NACA RM E58G10a C ONFIDENTTAL
? N
u)
N
N. N
'4 rl
N
rl
? 'r- ' 4 ' 9 0 ? 0
51
CD k 0
n 0
t (d a V P) m k 0
I
a, N
aJ
M 9 2
CONFIDENTIAL
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......................... . . .... 0 . . 0 . 0 .
........ . 0 . . 0 . 0 . 0 . ...... . . . . . . . . . . . . . . . . . ....................... .......... . 0 . . 0 . . . 0 . 0 .
52 CONFIDENTLAL NACA RM E58G10a
0
M
? N
a N
d! N
N
N
(D
rl
-! ri
N
ri
9 ri
ri
k 0 +, CJ a, *W (u
. r i k
k 0
C 0
k v i cd rd c cd
I
0, N
2 d R
....................... .......... . .... . . . . . . . . . . . . . . . . ........ * a .................... . * 0 .
0 . 0 . . . . * . 0 . 0 . . ...... . 0 . 0 . 0
0 . . ~ ~ ~ ~ I D E N T I A L
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......................... . 0 . . 0 . . 0 . 0 . b . . 0 . . ........ . . . . . . . . . . . . . . . . . ...... .......... ....................... . . . . .... . 0 . 0 . . 0 . 0 .
NACA RM E58G10a CONFIDENTIAL 53
^ . (a) Mach number, 1.35. u t
i! ( b ) Mach number, 1.0.
Secondary-flow r a t i o - WS 12 ' WP
(c) Mach number, 0.8.
Figure 30. - A i r in jec t ion compared with high secondary flow with e j ec to r 1 and no afterburning.
0 . ................................. m . moo 0 . . 0. m e em.. : 0 . 0 . 0 . 0 . 0 . . 0 . . ...... . ........ 0 . . 0 . . .........................
CONFIDENTIAL
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54
1
1
1
0
......................... ........ . . . . 0 . 0 . 0 . 0 . . 0 . . ...... . . . . . . . . . . . . . . . . . . . . . . . .... . 0 . . 0 . 0 . ....................... ..........
C ONF IDENT IAL NACA RM E58G10a
1
1
1.. 1.0 1.2 1.4 1.6 1.8 2.0 2.2 2.4 2.6 2.8 3.0 .8
Mach number,
Figure 31. - Expansion-ratio schedule of e j ec to r 7.
1
..- Mach number,
Figure 32. - Effect of design compromises of variable-geometry e j e c t o r 7. Secondary-flow r a t i o , 0.02.
.......... .......... . . . . . . . . . . . . . . . . . ....................... . . 0 . 0 .
0 . 0 . . . .
CONFIDENTIAL
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......................... . 0 . . 0 . . 0 . 0 . 0 . . 0 . . ........ . . . . . . . . . . . . . . . . . ...... 0 . 0 . 0 . . . .... . 0 . 0 . . .......... .......................
NACA RM E58G10a CONFIDENTIAL
9 M
? N
t cu
N
cu
co ri
55
a
k 0
N
rl
?
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0 . 0 . . 0 . . .... . 0 . . 0 . . ........ ...... . . . . . .............
56
....................... . . 0 . 0 . 0 . . . . . . . . . . . . . . . . 0 . . 0 . 0 . .......... .......... CONFIDENTIAL NACA RM E58G10a
0
a)
k 0 +, 0 a, ‘T I W
e +, a, E 0 W M a,
I i
a r t
I
% 2 k- k 0
a,
ti k 0 k k a, Pi I
+ m a, k 3 M .d ki
- -~ CONFIDENTIAL
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NACA RM E58G10a CONFIDENTIAL
cu N
(D
ri
cu rl
57
? Fv
a k d 0 0 a, m I
In K)
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58
9 ?
CONFIDENTIAL NACA RM E58G10a
Cn
k 0 -P 0 aJ ‘T3 a,
e t-’ a,
a, M I a,
l-i
P (d Ti k (d + k 0 a, u
F! 0 k k aJ PI I
(D M
a, k
rl & k
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NACA RM E58G10a CONFIDENTIAL 59
9 K)
N 9 0
0 .ti .p ai k ?
N
A !d a c 0 U W m
W
N
rn a,
R Y c , cu ri 0 c, 0 rl
9 N
m k 0 .p U W *T-J e,
6 % a, P
"9 ri
a *ri k R k 0
W
4
h
W 9 5 I + * 4 2
a a, P 5 a
0 0 I
k a,
@ a r- trl
a, k 3 bo
Y ri
1 k 0 9
rl N
ri c1 U a, k
8 l
a) M
9 ri ?
a, k 5 bD .d k -? W
9 ? ? d
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. . . . . . . ......................... ........ . . . . . . . . . . ...... . . . . . . . . . . . . . . . . . . . . . . . .... . . . . . . . . ................... ..,a . .......... 60
cu ri
CONFIDENTIAL NACA RM E58G10a
-%
0
A * $ ? g
k
V a, m
cu ?
,o ri
0 @.I
(D rl
m ri
k 0 * u a, c3 a,
k 0
a, u
i4 k 0 k
R
0
$ n
ri k
h
a 2 0 a, m k 0
:: Q) E I
0 + e,
d 2 k
....................... . .......... . . . . . . . .... . . . . . . . . . . . . . . . . . . . . . . . . . . '..'c*-&p&~ml .............. . . . . ...... . . . . . . ........ NACA - Langley Field, va,
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- - 0 rl rl
k 0 -P 0 a, '3 a,
k 0 -P d
0 a, 'TI a,
0 a, "3 a,
a, P k
0 +i 0 a,
k 0
d 0
$ 0
5 a
0 cu k 0
- - a, P
a, P 0 4 m
2 m
0 cu
.. 3
.. dc d
" LD dc 0
5 -P Ld
I
0 m
660s