development of natops performance software for the sh-3d

DUDI t KNOX LIBRARY

r AVAL POSTGRADUATE SCHOOL

MONTEREY, CALIFORNIA 93943

NAVAL POSTGRADUATE SCHOOL

Monterey, California

THESISDEVELOPMENT OF

NATOPS PERFORMANCE SOFTWAREFOR THE

SH-3D AND SH-3H HELICOPTERS

by

John Thomas Curtis

March 1985

Thesis Advisor: Donald M. Layton

Approved for public release; distribution unlimited

T222101

SECURITY CLASSIFICATION OF THIS PAGE (Whan Data Entered)

REPORT DOCUMENTATION PAGEI. REPORT NUMBER 2. GOVT ACCESSION NO

4. TITLE (and Subtitle)

Development of NATOPS Performance Software for

the SH-3D and SH-3H Helicopters

READ INSTRUCTIONSBEFORE COMPLETING FORM

3. RECIPIENT'S CATALOG NUMBER

5. TYPE OF REPORT & PERIOD COVERED

Master's ThesisMarch 1985

6. PERFORMING ORG. REPORT NUMBER

7. AUTHORfsj

John Thomas Curtis

8. CONTRACT OR GRANT NUMBERfa)

9. PERFORMING ORGANIZATION NAME AND ADDRESS

Naval Postgraduate SchoolMonterey, California 93943

10. PROGRAM ELEMENT, PROJECT, TASKAREA & WORK UNIT NUMBERS

tt. CONTROLLING OFFICE NAME AND ADDRESS

Naval Postgraduate SchoolMonterey, California 93943

12. REPORT DATE

March 198513. NUMBER OF PAGES

106U. MONITORING AGENCY NAME 4 AODRESSf// dl Iterant from Controlling Office) 15. SECURITY CLASS, (ot thla report)

UNCLASSIFIED15a. DECLASSIFICATION/ DOWNGRADING

SCHEDULE

16. OlSTRIBUTION STATEMENT (of this Report)

Approved for public release; distribution unlimited.

17. DISTRIBUTION STATEMENT (of the abatract entered In Block 20, It different from Report)

18. SUPPLEMENTARY NOTES

19. KEY WORDS (Continue on reverse aide It neceasary and Identity by block number)

NATOPS ComputerizationPerformance PlanningFlight PlanningHP-41CV Programs

SH-3 HelicopterHelicopter Performance DataHand-Held CalculatorsCurve Fitting

20. ABSTRACT (Continue on reverse aide If neceaaary and Identity by block number)

This thesis generates closed form equations for significant and fre-quently used NATOPS performance charts for the SH-3D and SH-3H helicoptersThese equations are developed Into interactive software for the Hewlett-Packard HP-41CV hand-held programmable calculator. With this softwareinstalled in the calculator the user is able to calculate numerous NATOPSperformance parameters (expeditiously, with reduced risk of error) bothprior to and in flight.

dd ,;FORM ,.7,AN 73 14/3 EDITION OF 1 NOV 65 IS OBSOLETE

S/N 0102- LF- 014- 6601SECURITY CLASSIFICATION OF THIS PAGE (When Data Entered)

Approved for public release; distribution is unlimited.

Development of NATOPS Performance Softwarefor the SH-3D and SB-3H Helicopters

by

John Thomas CurtisLieutenant Commander, United States Navy

B.A-, University of Georgia, 1973M.A. , Central Michigan University, 1931

Submitted in partial fulfillment of therequirements for the degree of

MASTER OF SCIENCE IN AERONAUTICAL ENGINEERING

from the

NAVAL POSTGRADUATE SCHOOLMarch 19 85

ABSTRACT

This thesis generates closed form equations for signifi-

cant and frequently used NATOPS performance charts for the

SH-3L and SH-3H helicopters. These equations are developed

into interactive software for the Hewlett-Packard HP-41CV

hand-held programmable calculator. With this software

installed in the calculator the user is able to calculate

numerous NATOPS performance parameters (expeditiously, with

reduced risk of error) both prior to and in flight.

DUDLEY VCNW yjiE SCH0

0L

TABLE OF CONTENTS

I. INTRODUCTION

A. COORDINATION OF EFFORT •

B. BACKGROUND

C. GOALS •

10

II. APPROACH TO THE PROBLEM 11

III. THE SOLUTION 15

A. EXAMPLE SURFACE REGRESSION ANALYSIS 15

IV. RESULTS18

V. CONCLUSIONS AND RECOMMENDATIONS 20

APPENDIX A: NATOPS PERFORMANCE SOFTWARE USER'S GUIDE . .21

A. BASIC USE 21

B. SUPPLEMENTARY PROGRAMS 24

C. GENERAL USER INFORMATION 24

D. INITIAL CALCULATOR PREPARATION 25

E. CALCULATOR FLAGS 26

F. CALCULATOR MEMORY REGISTERS 27

APPENDIX B: REGRESSION EQUATIONS AND SOFTWARE

DOCUMENTATION 28

A. ENGINE PERFORMANCE - TOPPING (721°C T5) ... 29

B. LOW PITCH AUTO RPM 34

C. SINGLE ENGINE HATER TAKEOFF 37

D. AIRSPEED CALIBRATION 40

E. TEMPERATURE CONVERSION 41

F. DENSITY ALTITUDE UU

G. BLADE STALL 47

H. ENGINE PERFORMANCE - MILITARY (696°C T5) ... 52

I. ENGINE PERFORMANCE - NORMAL (660°C T5) .... 55

J. TORQUE TO HOVER IN GROUND EFFECT 59

K. TORQUE TO HOVER OUT OF GROUND EFFECT 62

L. MAXIMUM RANGE - TWO ENGINES . 65

M. MAXIMUM ENDURANCE - TWO ENGINES 70

N. ABILITY TO MAINTAIN FLIGHT - ONE ENGINE ... 75

0. MAXIMUM RANGE - ONE ENGINE 81

P. MAXIMUM ENDURANCE - ONE ENGINE 86

Q. GROUND ROLL - POWER OFF 91

R. MASTER PROGRAM 94

S. PRINT PROGRAM 102

LIST OF REFERENCES 105

INITIAL DISTRIBUTION IIST 106

LIST OF TABLES

I NATOPS Performance Chart Reference 21

II Supplementary NATOPS Performance Chart

Reference 25

III Variable Abbreviations 28

LIST OP FIGURES

3.1 Engine Performance-Military Power (6 96°C T5) ... 17

A.1 Hewlett-Packard HP-41CV Calculator 22

ACKNOWLEDGEMENTS

The patience, support and understanding of my wife,

Debbie, and my children, Erik and Kelli, were instrumental

in the completion of this thesis.

8

I. INTRO DOCTION

A- COORDINATION OF EFFORT

A similar software development for the H-46D helicopter

was conducted at the same time as this development by Caram

[Ref. 1 ]- Because of the nature and complexity of the

problem, the initial stages of these investigations were a

joint effort. As a result, the Approach to the Problem

(Chapter II) and the basic method of Solution (Chapter III)

of this work and of Reference 1 are very similar-

B. BACKGROUND

Performance planning is an essential task to ensure the

safe conduct of flight for aircrew flying any aircraft.

Naval aircrew use the Naval Air Training and Operating

Procedure Standardization (NATOPS) manual to acquire all

necessary performance data. Foe the most part, NATOPS

performance information is presented in a graphical format

often requiring the user to transit several subcharts, which

may be located on different pages, to obtain the desired

performance parameter. This procedure is time consuming,

prone to error, and impractical in flight.

The purpose of this thesis is to correct these NATOPS

deficiencies by transforming selected performance charts

into interactive, user-friendly, computer software for a

hand-held programmable calculator. This solution would

enable aircrew to obtain performance data with increased

accuracy, reduced time and effort, and also permit use in

flight.

Previously there have been several succesful efforts in

NATOPS computerization. The most recent study [Ref. 2]

developed software for the A- 6 aircraft utilizing the

Hewlett-Packard HP-4 1CV hand-held programmable calculator.

This research demonstrated the feasibility of NATOPS

performance data computerization.

C. GOALS

The first goal of this study was to generate a closed

form equation for each selected NATOPS chart or subchart.

The equations were required to be of a form such that inde-

pendent variables were the specific chart input parameters

and the dependent variable, the output parameter. The equa-

tions used to "fit" each NATOPS chart had to allow an

explicit calculation of the dependent variable.

Furthermore, they had to consist of standard functions (no

differential/integral equations) which could be programmed

on a calculator or computer.

Once the equations representing the performance charts

had been derived, it was necessary to select the hardware

which would be used for software design. The HP-41CV

programmable calculator augmented with an extended functions

module and two extended memory modules was selected. This

selection was based on the small size, relatively large

memory capacity (6.4 K) and the successful use in the past

of the HP-U1CV.

Upon completion of the software development the ultimate

goal of this research was the testing of that software by a

Fleet Replacement Squadron (FRS) or fleet squadron for

fleet-wide implementation.

10

II. APPROACH TO THE PROBLEM

The overriding problem encountered was the generation of

closed form equations which accurately represented each

performance chart with the minimum number of terms.

Minimizing the number of terms was desirable because of the

calculator's limited memory space. For the majority of

charts considered there were two independent input variables

that yielded a single dependent output variable- This was

visualized as a three dimensional surface in space.

The fitting of an equation to an arbitrary surface

required the utilization of a numerical regression computer

routine. These routines are numerous and have been devel-

oped into several software packages for mainframe computers.

The software chosen for this study was the Biomedical

Computer Program (BMDP) statistical package [Ref. 3],

installed on an IBM 3033 mainframe computer located at the

Naval Postgraduate School, Monterey, California.

A regression is linear in nature no matter how many

independent variables are involved. However, nonlinear

functions may be used in a regression if they are first

"linearized". For example, if the nonlinear functions x 2,

x 3, and In (x) are transformed into independent variables

D,Y, and Z, respectively, then a regression can be performed

to yield an equation of the form

S = aU + bY + cZ + d (eqn 2.1)

where a, b, and c, are the regression coefficients, d is the

intercept, and S is the dependent variable.

The specific BMDP program used for a majority of charts

analyzed was the "all possible subsets" multiple regression

11

program (P9R) which allows the user to input a large selec-

tion of transformed independent variables to be examined

during the regression analysis. The P9R program included an

option to either use all the transformed variables offered

(method is none) , or perform the regression selecting

subsets of the offered transforms and output the subset with

the best fit statistics (method is Cp) .

The dominating criteria used to determine the best fit

statistics was the squared multiple regression correlation

(R 2 ). Accuracy was gauged by how close R 2 was to the ideal

value of 1.0. The required R 2 for an acceptable fit was

found to vary between performance charts, and was a function

of what dependent output variable was being generated, the

"irregularity" of the surface, and the number of independent

input variables. For each chart, multiple regression anal-

yses were performed varying the offered transforms in number

and/or type, until a closed form equation was generated that

yielded output that was within the accuracy of manual chart

interpolation. From experience it was found that an R 2

value of .99900 (or greater) yielded a sufficiently accurate

fit.

The accuracy with which a NATOPS chart could be read was

subject to the design of the individual chart. In general,

the following tolerances for dependent variables were estab-

lished (for the regression analysis)

.

airspeed: ±2 KIAS

indicated torque: ±1 %

unit range: +.0 01 NM/LB

fuel consumption: ±10 LB/HR

ground roll: ±10 FT

Prior to the execution of the regression program, a data

file for each surface was created. The file consisted of

data sets which were merely the independent variable values

12

and the corresponding dependent variable value. For a three

dimensional surface each data set consisted of three values.

It was critical to ensure that the data sets extracted from

a performance chart were as accurate as possible and that

the data file clearly defined the surface. Obviously, those

surfaces that contained "irregularities" required signifi-

cantly more data sets than smoother or more "well behaved"

surfaces. If a surface contained a sharp point or disconti-

nuity, this portion of the surface was eliminated from the

regression analysis due to the inability of the software to

accurately fit abberations.

The tranformed variable selection was the key to

successful regression analysis. Through experience one

gained an intuitive feel for what type of transformed vari-

ables would yield a close fit to a surface. Fortunately,

most of the surfaces responded well to regression analysis

utilizing combinations of the independent variables raised

to powers between one and four (polonomial regression) . A

standard polonomial regression program was developed

containing all the possible polonomial terms up to fourth

order. This standard program was used as a first attempt

for fitting all charts.

For a few surfaces, obtaining a close fit by regression

analysis was not possible without retaining an unacceptably

large number of terms. An alternative to this was to fit

each of the depicted influence curves and develop the final

computer software to interpolate between curves. The trade

off with an interpolation scheme was increased accuracy at

the expense of increased calculator program complexity. Two

examples of this method are the calculator programs "WTR

T/0" and "SE RNG" found in Appendix B. Additionally, in a

few cases it became necessary to use other transforms of the

independent variables such as exponentials and/or high order

fractional combinations of terms.

13

On the first execution of each regression analysis

"method is none" was selected in the ?9E program. This

instructed the BHDP software to use all offered transforms

for the regression analysis. During execution, matrix

algebra was performed with the independent variables and

transforms. If this algebra created numbers outside the

tolerance range specified in the program (default tolerance

= .0001) , the "method is none" option would eliminate the

offending variable, or transform, and continue execution.

The resulting output contained the E 2 value along with other

fit statistics and listed all terms eliminated for low

tolerance. Performing a second iteration with the out-of-

tolerance transforms eliminated, and with "method is Cp"

selected, allowed the BMDP software to analyze subsets of

the remaining transforms. Performing this two step process

yielded the best fit with fewest terms for each surface.

14

III. THE SOLUTION

The polynomial transform program yielded acceptable

regression results in the majority of cases. For the

performance charts that had difficult surfaces to fit (R 2 >

.99900 could not be achieved) , accuracy demanded that influ-

ence lines be fit individually and interpolation be

performed between them.

A. EXAMPLE SOHFACE BEGRESSION ANALYSIS

An engine performance chart (Figure 3.1) was chosen to

illustrate the regression technique since it demonstrates

the capability of numerical regression to generate an accu-

rate closed form equation while also showing procedures for

handling surface discontinuities.

The first step in the solution of this performance chart

was to create the data file for the regression program-

Data sets were taken along each pressure altitude influence

line at increments of 20° centigrade (C) with additional

points added for the sea level and 1000 foot altitude lines,

due to their discontinuities. Also, a data set was included

on each end of an influence line for accuracy. Each of the

75 data sets consisted of two independent variables (temper-

ature and altitude) and the resulting dependent variable

(torque). The flattened parts of the sea level and 1000

foot lines were omitted because of their discontinuities at

ambient temperatures at or below -20° C.

A numerical regression was performed with the "method is

none" option selected and using the standard fourth order

polynomial program (22 transforms) discussed earlier. The

resulting output listed the terms excluded from the

15

regression analysis due to exceeding tolerance limits (6) ,

the regression R 2 (.99965), and other fit statistics. The

high R 2 value indicated that the selected polonomial trans-

forms were representative of the surface.

The next step was to determine if some of the retained

transforms could be eliminated without significantly

effecting the fit. The six out-of- tolerance terms were

deleted from the transform selection and the program was

executed with the "method is Cp" option in effect. This

resulted in an elimination of 10 more transforms while only

degrading the R 2 value to .99952.

The equation for the surface was tested by writing a

program stub with which all data points were checked to

ensure accuracy. Since the surface could not be fit in its

entirety, an interpolation routine was required in the final

calculator program to calculate torque when the pressure

altitude was between 2000 feet and sea level at ambient

temperatures at or below -20° C.

16

NAVAIR01-230HLH-1 Section XI

STANDARD DATA

MODEL: SH-3HDATA AS OF 15 JANUARY 1983DATA BASIS. CALCULATED

ENGINE PERFORMANCEMILITARY POWER 696°C T5 OR 101% Ng

STATIC CONDITION ANTI-ICE OFF 100% Nf

ICE SHIELD (AFC 321) INSTALLED

ENG: (2) T58-GE10FUEL: JP-4/JP-5FUEL DENS. 6.5/6.8 LB/GAL

t\

Ul3sp

— — -- ....

—NOTES:(1) REDUCE AVAILABLE TORQUE

BY 6% WITH ENG. ANTI ICE ON- (2) REDUCE AVAILABLE TORQUE

BY 2% WITH ICE SHIELD (AFC 247)

INSTALLED

(3) TOPPING TORQUE REDUCTION

„ _

——

IN FORWARD FLIGHT

"" IAS-KTS 90 100 110 120

^»VN %NO. 1 ENG 1.5 2.1 2.8 15

....

% NO. 2 ENG 0.5 1.1 1 5 2.3

— \-

—1

- -

s k

\

^

^

s- _S s \

PF"'

Al

ESSUREET~"

—

-

-^TITUDE-- FE

in »-

— —r A

N

vO

—--\\

— \4v>\ o

\\

X;\\« v \>A—

\ V— —^b

\V

n;

v^ \\-

— £

- -

>^.

S^V

-— ....

.

—

"1 1 i 1

40 30 20 10 20 30 40 50 60"C

I ' I ' I ' I ' I ' I ' I ' I'

I ' I

40 -20 20 40 60 80 100 120 140"20 40 60

AMBIENT TEMPERATURE

Figure 1 1-6. Engine Performance-Military Power (696°C T5 ) Chart

120 140°F

S 33889 (Rl)

I

11-11

Figure 3.1 Engine Performance-Military Power (696 °C T5)

17

IV. RESULTS

At the onset of this study 16 different NATOPS perform-

ance charts were selected for computerization based on their

significance and frequency of use. It was anticipated that

the final performance chart programs would be too voluminous

to be collectively stored in the HP-41CV memory. This would

have necessitated using an external mass storage device or

executing individual programs piecemeal. Both of these

alternatives would have had unacceptable detrimental

effects. The only other alternative would have been that of

contracting Hewlett-Packard to develop one or more plug-in

applications modules containing the NATOPS software.

Fortunately, the majority of programs were reasonable in

length and could reside in the HP-41CV f s memory (augmented

with extended memory) simultaneouly. A master program named

"FLIGHT" was written which functioned as a software manager

and assigned performance charts to specific calculator key

locations (Appendix A). The master program tranf erred subor-

dinate programs from inexecutable extended memory to the

executable work space in main memory, and interactively

communicated with the user.

Appendix A contains the simple user instructions to

execute any of the 10 listed NATOPS charts desired. With a

printer attached a complete performance profile can be

executed and printed for any mission plan. Appendix A also

contains a listing of supplementary performance charts

developed as stand-alone programs which could not reside

simultaneously in the calculator's memory. Appendix B lists

all surface regression equations, flow charts, and calculaor

program code. It should be noted that the regression equa-

tions can be programmed for use with any capable system.

18

The results presented in Appendix B are for the SH-3D and

SH-3H NATOPS performance charts referenced in Appendix A.

Future modification of these charts would invalidate the

performance software for those paticular charts.

19

V. CONCLUSIONS AND RECOMMEND.ANIONS

From the results of this thesis it can be concluded that

graphical NATDPS performance data can be computerized. To

effectively accomplish this, computer oriented numerical

regression routines must be utilized to generate closed form

equations.

Once the equations have been derived computer software

can be developed that executes the programs in an expedi-

tious, accurate, and portable fashion. Furthermore, this

software can be designed for virtually any type of computer

from hand-held programmable calculators to personal

computers.

It is recommended that the NATOPS performance software

developed in this study be submitted to a fleet squadron or

Fleet Replacement Squadron (FRS) for test and evaluation.

Since the software can be utilized as is, with off the shelf

Hewlett-Packard components, the cost of testing would be

minimized. If this software proves itself to be applicable

fleet-wide, Hewlett-Packard should be contracted to develop

plug-in application modules which would increase reliability

and decrease execution time.

20

APPENDII A

NATOPS PERFOBMANCE SOFTWARE USER'S GDIDE

A. BASIC USE

The NATOPS performance software designed for the HP-41CV

calculator is simple and expeditious to use. The calculator

keyboard configuration is depicted in Figure A. 1. As you

can see, the first top two rows have abbreviated program

names over the keys. The exact meaning of each performance

chart abbreviation and its NATOPS [Ref. 4] figure reference

are contained in Table I below.

TABLE I

NATOPS Performance Chart Reference

NATOPS CHARTTITLE

Density Altitude Chart

Engine Performance-MilitaryPower (696°C T5) Chart

Indicated Torgue to Hover inGround Effect- 10 Feet Chart

Indicated Torgue to Hoverout of Ground Effect Chart

Blade Stall Chart

Maximum Range-Two- Engine Chart

Maximum Endurance-Two-Engine Chart

Single Engine EaterTakeoff Chart

Maximum Range-One-Engine Chart

Maximum Endurance-One- Engine Chart

HP-41CVPROGRAM TITLE

DA

E PERF

IGE

OGE

STALL

RNG

ENDR

WTR T/O

5E RNG

SE ENDR

NATOPS FIGURENUMBER

11 -3

11 -6

11 -8

11 -9

11 -5

1 1 -13

11 -16

5- 9

11 -24

11 -25

21

jON

J(USER JPRGM jJALPm

PP/DA E PERF IGE/OGE STALL RNG/ENDRDD.DDDWTR T/Q SERNG SEENDR .DDDDDD B'DO D

BDQDQQQa aa aa a

Figure A. 1 Hewlett-Packard HP-41CV Calculator

22

The programs listed in Table I are assigned to the

corresponding keys shown in Figure A.1. The key marked "pp"

(Preflight Planning) executes all 10 programs successively

and produces a hard copy of the output. This program

requires that a printer is attached. To execute a program

follow the steps presented below.

1. Turn the calculator on.

2. Press the •XEQ 1 key. At this point "XEQ _ _" will be

displayed. Press the 'ALPHA* key and observe "XEQ _"

and the word "ALPHA" in the display. Type in the

word "FLIGHT" and again press the 'ALPHA 1 key. You

will see "PRGM" flash in the display followed by a

constant "READY".

3. Find the key with the paticular performance chart

desired and push it. As the program is initiated the

calculator will prompt the user for any needed infor-

mation. The exact prompt meanings are defined below:

• PA? (FT) - pressure altitude in FT.

• DA? (FT) - density altitude in FT.

• OAT? (C) - outside air temperature in °C.

• GWT? (LB) - gross weight in LB.

• WIND? (KT) - head wind in KT.

• NR? {%) - rotor RPM in per cent.

• <BANK? (DEG) - angle of bank in degrees.

• FUEL? (LB) - fuel on board in LB.

4. Answer the prompt by pushing the corresponding

numbered keys until the desired value is seen in the

display. If a mistake is made, simply push the key

with the horizontal arrow (far right column, four

keys from the top) and re-enter the number. If the

number to be entered is negative (negative OAT) , push

the key marked CHS after the number has been entered

in the display. When the desired number is displayed

in the window push the key marked R/S (run/stop,

bottom right key) .

23

5. After all the prompts required have been answered the

calculator will execute the program. While the

calcualtor is working "PEGM" will be visible in the

display. As the calculator generates answers they

are shown in the display. Some charts yield more

than one performance parameter, so it is necessary to

note each parameter displayed and then push the E/S

key to continue execution.

6. Once all performance parameters have been calculated,

pushing E/S will display "EEADY" which tells the user

he has been given all available output and the calcu-

lator is ready to execute the next program.

7. Before executing the "pp" program ensure the calcu-

lator is turned off. With the printer also turned

off, plug the printer input chord into the only

remaining extension port. Turn the calculator and

printer on, select the normal mode on the printer,

and push the "pp" key. All other instructions remain

the same.

B. SUPPLEMENTARY PROGRAMS

In addition to the performance charts listei in Table I,

six additional charts have been computerized and listed in

Table II. Due to their large sizes and/or aplicability only

to Functional Checkf lights, they were developed strictly as

stand-alone programs. They must be loaded and executed as

discussed in Section D of this Appendix. After execution

begins, these programs will appear to the user to operate

exactly like the programs listed in Table I.

C. GENERAL USER INFORMATION

The NATOPS software should generate accurate answers

within the range of a selected performance chart. If data

24

NATOPS FIGURENUMBER

3- 12

3- 14

11 -2

11 -7

11 -22

11 -26

TABLE II

Supplementary NATOPS Performance Chart Reference

HP-41CV NATOPS CHARTPROGRAM TITLE TITLE

MIN Q Engine Performance-ToppingPower (721°C T5) Chart

RPM Low Pitch AutorotativeEPM Chart

TEMP Temperature ConversionChart

NP Q Engine Performance-NormalPower (660°C T5) Chart

ENYLP Ability to Maintain LevelFlight One-Engine Chart

ROLL Landing Distance GroundRoll-Power Off Chart

is entered erroneously, or in excess of a paticular chart*

s

range, the output will be in error.

In the cases where a chart has limitations such as

Ability to Maintain Level Flight - One-Engine Chart [Ref. 4:

p. 11-37], these have been taken into account within the

program and the output will tell the user if they exceed

that limitation. If the user is ever in doubt as to the

validity of the calculator generated performance data, the

NATOPS manual should be consulted.

D. IHITIAL CALCULATOR PREPARATION

The basic use instructions assume the user has a calcua-

lator that has all the performance software installed. If

the user merely has the calculator (with two extended memory

modules and an extended functions module) , a card reader,

and the NATOPS software program cards; several steps must be

taken before the calculator can be used as described

earlier.

25

1. Become familiar with the HP-41CV owner's manual and

the operating instructions of all peripherals. While

the occasional user can avoid an in depth knowledge

of the system, initial set up requires someone who is

familiar with the hardware and procedures listed in

References 5,6, and 7.

2. With the extended memory and extended functions

modules in their proper ports, and with the card

reader attached, loading the programs into main and

extended memory can begin.

• Load the following programs into extended memory:

"DA, E PERF, IGE, OGE, STALL, RNG, ENDR, WTR T/0,

SE RNG, and SE ENDR".

• Load "FLIGHT" into main memory. You may also load

"TEMP" if required.

3. Ensure the only programs in main memory are the ones

listed above and erase any other programs.

4. Pack the programs in main memory.

5. Execute the program "FLIGHT".

When "READY" appears in the display the calculator is

ready for program execution.

E. CALCULATOR FLAGS

Flags 1 through 3 are used for condition checking in the

execution of some programs. If the programs are always

allowed to run to completion (the user presses R/S until

"READY" appears in the display) these flags will be cleared.

If the user stops execution before completion and executes

another program, there is a possibility that the second

program will produce an output that is in error.

26

F. CALCULATOR HEHOBY REGISTERS

Memory registers and their contents are shown below

Re gister s

00-070809101112-141516171819202122232425262728293031323334353637383940414243

Cont ents

ScratchPAGWTDAWindScratchOAT) 2

OAT) 3

OAT) *

PAiPA<

,

iPA'PA'GCT_'GWT'GWT','gwt:GWT) 6

2

34S

24

'DA) $

'Find]'WindOATHIGE QHOGE QBlade Stall KIASMax Range KIASMax Range Unit RangeMax Endurance KIASMax Endurance FuelEngine PerformanceWater Takeoff KIASS/E Max Range KIASS/E Max Range UnitS/E Max EnduranceS/E Max Endurance

Consumption(Military) Q

RangeKIASFuel Consumption

Note: An explanation of abbreviations

Appendix B.

may be found in

27

APPENDIX B

REGRESSION EQUATIONS AND SOFTWARE DOCUMENTATION

This appendix contains all regression equations and

curve fits generated for each NATOPS chart considered. It

also contains the associated calculator program code, flow

charts, and the tested accuracy of the output. Although

regression equations are of the form shown in equation 2.1,

they are presented in tabular form due to their large sizes.

The flow charts use standard symbology and depict the

general programming logic but little detail. The computer

code listings are in the Reverse Polish Notation (RIN)

language developed by Hewlett-Packard.

TABLE III

Variable Abbreviations

ABBRE VIATION OUABLE UNIT

3Ii "ith" Base Line(number omitted if only one)

(K)CAS Calibrated Air Speed KT

DA Density Altitude FT

EAS Equivalent Air Speed KT

GttT Gross height LB

(K) IAS Indicated Air Speed KT

Nr Rotor Speed RPM

OAT Outside Air Temperature °C

PA Pressure Altitude FT

Q Indicated Torque %

TAS True Air Speed KT

DR Unit Range NM/LB

28

A. ENGINE PERFORMANCE - TOPPING (721°C T5)

Program Title: MIN Q

Accuracy: ±*\% Q

Independent Variables:

A = PA/1000

B = OAT

Relationships:

For PA = sea level OAT < 10

Q = -.070 B + 119-7

For PA = sea level OAT > 10

Q = -.811 B + 127.1

For PA = 1000 OAT < -10

•Q = -.067 B + 119.3

For PA = 1000 -10 < OAT < 10

Q = -.250 B + 117.5

For PA = 1000 OAT > 10

Q = -.778 B + 122.8

For PA = 2000 OAT < -22

Q = -. 056 B + 1 18.8

For PA = 2000 -22 < OAT < 10

Q = 113.5 exp[-. 00248 B]

For PA =2000 OAT > 10

C = -.756 B + 118.3

For PA = 3000 OAT < -32

Q = -. 100 B + 116.3

29

Remainder of chart is regression equation with Q as the

dependent variable.

Term Coefficient

Intercept 122.151A -4.30544B -.378299A3B3 .316746 X 10" 7

A2 5.33051 X 10-2A2B -5-69557 X 10"*A2B« -.726407 X 10~»A3 1.27824 X 1

0"

2

AB2 2.19656 X 1 0~ *

B2 -7.45649 X 10-3B3 -9.76376 X 10~sB* • .228517 X 10-5

30

MIN Q

C START J

pa<iooot>—IIL

PA<20007>—I£L

NO

Lbl 08

CALCULATE

Q

YES

o-M K

OUTPUT

Q

C STOP "^

1DETERMINE

APPROPRIATEOAT

RANGE

CALCULATELOWER

Q VALUE

CALCULATEHIGHERQ VALUE

INTERPOLATE

31

81 LSI "HIH Q

82 i til fi

83 CF C i

84 "Ofi" "

95 48

86 XTOft

fi

87 "K85 41

89 yjnH

18 PROHPT

!! 5 ! 81

Id -pa»

13 48

14 i'ii ! U fi

15 "hFTi.i

16 41

17 XTO hi

is pro KPT

19 1 53 R

21 STO 82

di t

i

ni V •' • u£j ?••. .'

1

X)Y'J

L. J GTO 86/' r- XF9 r>

07(.1 STO 97

GTO D

29 * LSI 9b^.-.'.-i w

31 RCL 62

t~i / i

;

ii GIU h7

34 R

7CSTO 87

GTO

51

52

53

54

Xt2

STO 83

RCL 81

(t2

39 RCL 82

48 K>Y~

41 GTO 83

42 -32

^l RCL 81

44 X>Y

45 GTO 88i- urf,to f-Chi

r-

4? STO 67

48 GTO L'

49+LBL Ob

58 RCL 62

68

62

63

64

65

bo

f C

r4

STO 84

RCL 81

VtX

STO 85

RCL 81

*

STO 86

.228517 E-5

*

122.151

T

RCL 62

-4.36544

+

RCL 61

- 378299

+

RCL 82

YtX70 RCL 85

/ H *

m .31 6746 C_7L 1

* *

+

07 RCL 82

84 .85:33851

*

PCOb +

Q7 RCL 8300 rn-i

r.i.L 61

89 *

98 -.888569 CC"7J-Jl

91 *

92 +

Q < RCL 83

94 RCL 66

95 *

qc fit iO?E-3

9? *

98 +

99 RCL 61

166 RCL 82

181 *

182 .8127324

183 *

184 +

185 RCL 82

186 RCL 64

187 *

188 .688219656

189 *

118 +

111 RCL 84

112 -.88745649

113 *

114 +

115 RCL 85

116 -.88889763761 171 1

1

*

118 +

119 STO 87

128+LBL D

121 TONE 6

122 "HIH 9= "

107a. J fiRCL 67

124 I- V"

125 PROMPT

126 GTO -HIH 6"

127<LBL fi

128 1

129 RCL 62

138l."_C"ift-T '.

131 GTO H

132 X=8?

133 GTO 1

134 m H1 "?ciO-J XE6 I

136 RCL 95

137 -

138 RCL 82

139 *

148 RCL 85

141 +

142 STO 87

143 PTN

144* LBL B

145f\

146 RCL 82

147 X=Y?

148 GTO G

149 KEQ G

156 X'EQ H

32

151 RCL 841 c-.

153 RCL 62

154 1

iJJ -

156 *

157 RCL 64

158 +

159 STO 67

166 RTH

16ULBL p

162 3

163 RCL 82

164 K=V~>

165 GIGf

166 XEQ F

167 KEQ G

168 RCL 83

169 -

178 RCL 62

171 2

172 -

173 *

174 RCL 63

175 +

176 STO 87

177 RTH

178+LBL r

179 RCL 61

188 -.1

181 *

lO£ liO^

187 t

184 STO 63

185 RTH

186*LBL G

187 -22

188 PCL 81

i . fi•'

i

'

198 GTO 61

191 -.656

192 *

193 118.8

194 +

195 STO 64

196 RTH

197»LEL 81

198 16

199 RCL 81

286 K>Y?

LSI Ui'j " i.

283 *

264 EtX

265 113.49153

COO *

287 STO 8*

288 RTH

269*LBL 82

218 RCL 61

211 -.756

212 *

213 113.3

214 +

51 1; QTn pi£_ i J J ! U .

216 RTH

217*LBL H

219 RCL 61

226 X>Y?

221 GTO 63

222 -.667

223 *

224 119.3

225 t

226 STO 85

Ci-i r. h

228*L8L 63

229 10

238 RCL 81

231 zm232 GTO 04

234 *

236 *

237 STO 65

238 RTH

239*LBL 84

246 RCL 81

a i ~.((c

24? *

243 122.8

244 t

245 STO 65

246 RTHOil.! r«i t

eti*LbL i

243 18

249 RCL 61

256 JOY?

251 GTO 65

252 -.67

253 *

254 119.7

255 +

23b b i 06

257 RTH

258HBL 65

259 RCL 81

268 -.311

261 *

262 127.1

263 +

264 STO 86

265 ,EHB.

33

B. LOW PITCH AOTO RPB

Program Title: RPM

Accuracy; Exact


A = PA

B = CAT

C = GWT

D = Nr (for GWT = 17,000)

Relationship:

For the table value (GWT = 17,000)

D = [A + 1000]/500 + 100 + [B + 1 ]/5

The table value is corrected for the actual GWT by

Nr = 3.5[C/1000 - 17] + D

34

RPM

INPUTOAT, PA

CALCULATENr

(GWT=17,000)

INPUTGWT

CORRECTNr FOR

GWT

OUTPUTNr

C STOP J

35

81+LBL "RPH

82 FIX !

83 "OfiT ?

04 48

95 XTOfi

86 "hC°

87 41

98 KTOh

89 prokpt

18 STO 81

li "PS ?

12 46UTnnA i I'M

14 j-FT"IP

1

1

lb XTOfi

i I PRfSHPT4

i 1 E3

19 +

588

/

^^ 189.—. -T

+

•"i.4

it RCL 81

OPL.-J 18

2b t

.•jT cw !

'-

Cu

+

38u ,*.iit n

31 48

XTOfi

6 j"MS"

417C"

XTOP

.

J.h psfiMpT

4 .- RCL I

"*G v/w1899

41 17

42 -

* 7 7 c•J . J

*

5J f

46 "Hlfl HR=

47 hRCL X

48 PROMPT

49 GTO "RPH

59 END

36

C. SIHGIE ESGIHE WATER TAKEOFF

Program Title: WTR T/O

Accuracy: ±1 KIAS


A = OAT/10

B = GWT

Relationships: All influence lines are of the form

KIAS = 10 [a exp (b A) + c exp (d A) ]

GET a b c d

15,000 1.367275 -.588256 .385220 .55437216,000 1.741077 .098931 .015010 1.25030417,000 2.329929 .082539 .012430 1.31941118,000 2.715378 .082631 .027075 1.20507919,000 3.227943 .074984 .010291 1.67521820,000 3.792946 .070861 .003270 2.524752

Note: This program is not valid for GWT > 20,000. Also, if

the computed KIAS is greater than 70 KT, the display will

show 999 KT indicating an inaccurate output. If the

computed KIAS is less than 15 KT, the display will show 15

KT indicating that a takeoff is possible regardless of the

wind conditions.

37

WTR T/0

f START J

rDETERMINE

APPROPRIATEINFLUENCELINES

''

CALCULATEUPPER GWTLINE VALUE

v

CALCULATELOWER GWT

LINE VALUE

' i

INTERPOLATE

>'

C RETURN j

WTR T/O KIAS STORED R3g

38

Bl LBL -m. T/o

22 816 .828

83r t n

i U 86

64 *LBL 84

85 RCL 66

BO iNi

87 RCL 69

83 y / _ v •*

(W 1, i u d5

18 86

11 GTO 64

12rrnj i u 86

* "7

LBL 85

14 -

15 STO 87

16 XEQ INI 66171 ! XEQ

i XEQ 1*

i7 STfi 65

2 H i

"'1 C T _ 66

59 XEQ IHB 66

bV XEQ 17

24 XEQ 14-tC

RCL 85-

07 RCL 87

fa. V *

29 RCL 65

._! rj

16

75 *

*l^76

w«4 ?.<='!i *"i

7cGTO 86

RDHt .-

•J 1

<-

-i .-, yi ii

ft \ ~ T

•~

3?

STO 39

41 RTN

42* LBL 66i"7 Qh'5

44 STO 391C4 J RTH

46* ! £i 13

47 STO 63

48 RBH

49 r-Tf!62

RBH

51 STO 81

J -.2 RBNC7

STO 88C<J -t RTH

55LBL 14C ?•jb RCL 81C-7

RCL 38

JC> 18

59

68 STO 12

6 J±

62 FfX

t-i RCL 66

64 *

65 RCL 63

66 RCL 12

bl *

rjti.'C i ft

RCL 62

76 t

?'; +

7"l' L. * In

73*L£L 15

f 44 -1 f -i-^

I, 3b73

i Jcor, 7

76 70c51 '. - . a.

77 CCii

^"1ro RTN

79* LBL 16

86 1 7 j (

1

81 . 8S393

Gi- .81561rt-?

CO 1.2563C'A RTN

35* LBL 17

0£ - 77l_- '.' u 1 --! -_!

ft"?r .832539a00 .01243

39 1.31941

99 RTH

LBL 18

9P 2.7154

93 .63263

94iV07u7C

• V w 1 '_: 1 _'

95 1,2851

96 RTN

97* LBL 19

98 3.223i

-»n• ? 4

l

j d 4

1 89 .01829

181 1.67522

182 RTH

183*LBL 28

184 3.793

185 .67836

166 .88327

187 2.52475

168 .END.

39

D. AIRSPEED CALIBRATION

Program Title: (not developed as a separate program)

Accuracy: ±.25 KIAS

Relationship:

IAS = 1.03581 (CAS) - 5.530087

Note: The climb curve and the descent curve were not fit.

Although the level flight curve was not developed as a sepa-

rate program, the relationship was used in several other

programs to convert CAS to IAS.

40

E. TEMPERATURE COBVERSION

Program Title: TEMP

Accuracy: Exact


F = °F

C = °C

Relationships:

F = {9/5) C + 32

C = 5 (F - 32)/9

41

TEMP

INPUT•F

CALCULATE

-Conversion^

input

Icalculate

42

81 LBL "TEMP

82 FIX 1

83 Vt ill

84 °NEEB?

85 PROHPT

66 r 1. 1.' i- i-

e? CF 27

83 "BEG F ?"

89 PROHPT

18 32

11-

12 5

*

14 9

ft /

57 GTQ 81

1S+LBL E

1? CF 27

29 "BEG C ?"

•*jA

PROHPT':

9

£0 *

it j

cb ii

28 "BEG F=

29+LBL 81

38 fiRCL X

32 GTQ "TERP"

33 END

43

P. DENSITY ALTITUDE

Program Title: DA

Accuracy: Exact

Variables:

T = ratio of OAT to SSL temperature

P = ratio of atmospheric pressure to SSL pressure

D = ratio of air density to SSL density

H = actual tapeline altitude (FT)

Hr = DA

Hp = PA

k = temperature lapse rate for standard atmosphere

Relationships:

p = D T = T5-260S59 [Bef. 8]

T = [273.15 + OAT]/288. 15 = 1 - k H

P = [1 - k Hp] S - 260559

D = [1 - k Hr]*-260S59

TAS = D~ - 5 EAS [Bef. 9]

44

DA

C STARTJ

CALCULATEDA, CNV F

C RETURNJ

DA STORED R10

45

81'LBL "Df

62 PCL 88

83 b. 863 E

84ftC

*

r.

j

8t 1

1

87 +

68 •J . i

!

>85S

89 vtx

18 RCL 38077£. 1 -J i , i J

101 <_ f

1 7 000 ( c1 -' t- '-1 '_' ] 1 J 'J

14

1c

.

10 STQ MH

174 1

07.-L7! *

10U4Ui i

.'

4. .- CHS

2§ 1

19

46

G. BLADE STALL

Program Title: STALL

Accuracy: ±2 KIAS

Upper Chart


A = PA/1000

E = OAT

Relationship: Eegression equation with BL1 as the

dependent variable.

Term Coefficient

Intercept 5.56893A -.223872B -5.56144 X 10-2A 3 1.09302 X 10-3A2 -1.99009 X 10-2A2B -5.58699 X 10-*A2B2 1.72716 X 10-sA2B3 * .581095 X 10~*A23* -.135402 X 10-*AB 7.82900 X 1

0"

3

AB2 -2.47111 X 10-*A3 3 -.744059 X 10~sAB* .182777 X 10-6B2 8.76430 X 10"*B3 1.96684 X 10-sB* -.525713 X 10-6

Second Chart


A = BL1

B = Nr

Relationship: Regression equation with BL2 as the

dependent variable.

Term Coefficie nt

Intercept -20.000000A 1.000000B .200000AB* . 164047 X 10~22B3 -.472667 X 10-»*

47

Third Chart

Independent Variables;

A = GWT/1000

B = BL2

Relationships: Eegession equation with BL3 as the

dependent variable.

Term Coeffic ient

Intercept 10-396600A -.599.163B 1.00460A2 7.47972 X 10"2

Bottom Chart


A = angle of bank

B = BL3

Relationship: Eegession equation with CAS as the depen-

dent variable.

Term Coefficient

Intercept -7.79009 X 10~ 2

A -.120130B 20.0189A* -.327492 X 1 0~

s

A2 -1.22325 X 10-2AB -7.49109 X 10~2AB2 1.39609 X 10~2AB3 -7.73984 X 10~*

48

STALL

C START J

CALCULATEBLj

CALCULATEBL„

ICALCULATE

BU

ZJCALCULATE

CAS

ICALCULATE

IAS

f RETURN \

BLADE STALL KIAS STORED R33

49

81ii pi it

* t r\ !

i hi!

.L

82 RCL 88

i — _ -J '_ i £.

64 *

85c cJ . J6393

86 +

87 RCL 38

8S J. E

89 ¥

18 +

11 RCL 19

12 11 V 57 r_77 j C -j

*

H +

i rRCL 18

16 i. ?9 £-?

i { *

1 u +

19 RCL 18

28 Of 1

F.LL7.q

*

*

ilil= CO"? C_•J » J '-' 1 L.

.4

1:3 *

24 +

OC RCL 18

ic p.PfCL 15

L_01

:|"ji(lb t~

29 *

7Q t

7iRi.-L

^ nI

Vimr-.i

PAI 16-I™I

$

7,1J 7

CO'• J 11 E-6

7".*

7w +

77Ri 18

70RiI 17

70. *

48 -, 1354 E-7

*

42 +

43p. .-

Kl1

88J A

k(L. j»j

i:

46 1 1 829 E-3

47 i

43 t

49 RC1

68r.-4•J 13 PCj 1=;

.1 1*

w'l—

C7

68

61

62

-2.47111 E-4

*

+

RCL 88

RCL 16

*

-.7448759 E-5

RCL 88

RCL 17

in-i-!-> c £

, l&£( 1 1 fc.

_

h"i *

68

69

-n1 i

1 £

.• /

74

i -J

76

b'M

31

84

RCL 15

0. ( b^O t 1

t

+

RCL 16

1.96684 E-5

*

+

nr-i < 7P.LL i I

_ C-X717 p_i

+

ENTER!

28

KOYRCL 86

AC m36 *

«7.16 4847 E-22

;-( *

89 f

98 ML 88

91 7

'•-1 y U.t'..'

i i ft

07

94 1

95 +

96 RCL 88

97 1 u

98 *

+

188 1.013 46

181 t

182 18. 4

183 +

184 RCL 89

185 -.593163

186 *

187 f

163 RCL CL

1837 j

7972 C_7

118 t

111 +

112 STO 82

113 28. 8189

114 *

115-*

-.-. 79 E- ^

116 t

117 RCL 81

113 -.1 2813

119 *

128 f

121 RCL 81

led 4

f 01 YtX

iit _ 7'27492 E-5

125 *

126 +

127 RCL 81

123 V-*0

129 -i.'i-?3?c

- E-2

138 *

131 +

17-

Il-JL RCL

133 RCL 82

134 t

135 -7.49189 E-2

136 *

137 t

1701 -.' RCL 8217Q1 -'7 v+?

148 RCL 61

141 i.

142 1 7-:1 1 VI»689 E-2

143 #

+

145 RCL

146 7

147 YtX

148 RCL 81

143 *

158 _7 71 . 1

'3934 E-4

50

I EM ii J 1 *

J J£

153 ! 8358

j

\C:i

i c-i J : S'U :

.END.

51

H. ENGINE PERFORHANCE - MILITARY (696°C T5)

Program Title: E PEEF

Accuracy: ±1% Q


A = PA/1000

B = OAT

Relationships:

For PA = sea level OAT < -20

Q = -.05 B + 120.5

For PA = 1000 OAT < -32

Q = -.0938 B + 118

Remainder of chart is regression equation with Q as the

dependent variable.

Term Coefficient

Intercept 115.448A -3.76123B -.408791A2B 9.78404 X 10"*AB -9.34240 X 10"3AB3 .749596 X 10~sB2 -8.34115 X 10-3B3 -7.24488 X 10-sB* . 164096 X 10-5

52

E PERF

YES

NO

Lbl 04

CALCULATEQ @ 1000'

ILbl 05

CALCULATE

Q G> 2000'

IINTERPOLATE

Lbl 05CALCULATE

Q

YES

Lbl 03CALCULATE

Q @ SEA LVL

Lbl 05

CALCULATE

Q G> 1000'

IINTERPOLATE

—J

f RETURNJ

ENGINE PERFORMANCE Q

STORED R38

Lbl 03CALCULATE

Q (? SEA LVL

Lbl 04CALCULATE

@ 1000'

INTERPOLATE

53

0HLBL "E PER

82 S

83 RCL 88

84 H>Y?

65 GTO 82

86 -32

p.7 pfM 7j"|

9S K>Y?

89 GTO 81

18 XEQ 83

1 i FHTFv*& a L);! Li i

* n urn n*i • a h :.f vsm

13 -

14 RCL 88

15 *

i C _

i- err, to

IS PTN

19+LSL 81

28 -28

v i 9-' )¥•* *. '. : ". :

..: *

w C. h -:

T

23 GTO 85

24 RCL 98

^ STO Hi

0£ ft_ J_- i

27 STO 88

23 STO 1?

29 KE8 83

38 XEQ 85

3i-

32 RCL 61

33 * .

"7 .J Ti ;"• 1 rt ~i

it K*.L c*3

7cj „•

-_-i •j i u J'.:

?**i•j T L- 97

t?*LzL iVT1

46 £

41 RCL 98i -:

v1 \y

43 rin ftc

'i i y *_* -j

tt — 7*"!

4"i PC;-irt

4n U\U'

t 3* 1 - : i i 65

48 RCL 68

51 STO 68

5? y-io

53 STO 18

54 KEQ 94

J.i f-.t" DJ

56 -

16!

182

163

C7RCL 91

co

59 -

66 T

61 RCL ee-

63 CHS

64r-TS0:L' 38

65 GTO 67

66 L8L 63

67 RCL 38

-.85

-J j *

76 126cJ

71i i

+

i C STO 86

1 -J RTH

i t*LbL 84

I J RCL 38

76 -.6';>;

•5t .'

1 i•t

f 118

79 +

88 STO 68

i RTH

g9*| R| 65

J RCL 68

o4 -3.76123

*

861 c1 iD 448

£7 t

,-,J-,

RCL 36l~ l"

07 -.4* 18791

~i y'i *

01 +

.- £. RCL 18

'37 RCL 36

94 *

95 9.76484 E-4

96 *

+

98 RCL 88

IS*

186

167

168

189

118

111

it?

113

114

113* ' ci io

11

-9.3424 E-3

*

+

RCL 88

RCL 16

7.49596 E-6

*

+

RCL 15

-8.34115 E-3

*

RCL 16

-7.24488 E-5

+

RCL 17

1.64696 E-6

*

+

1

1

no119

128

121

122 STO 38

123 RTH

!24*LBL 87

125 RCL 81

126 STO 68

127 Xf210G CTfi {QI i--j •.' i 'j !

129 .END.

49 STO 6!_; i =_' V iRCL JVJ

Vii '.; 168 *

54

I, ENGINE PERFORHANCE - NOfiMAl (660°C T5)

Program Title: NP Q

Accuracy: ±'\% Q


A = PA/1000

B = OAT

Relationships:

For PA = sea level OAT < -18

Q = -.0568 B + 119.4800

For PA = sea level -18 < OAT < -7

Q = -.2727 B + 115.5914

Remainder of chart is regression eguation with Q as the

dependent variable.

Term Coefficient

Intercept 111.627A -5.76421B -.797907A«B2 .847954 X 1 0" &

A3 -.0144287A3B3 -.252248 X 1 0~&A2 .336850A2B 1.61809 X 10-3A2B2 -3.23450 X 10"*A2B3 .453896 X 1 0~sAB2 2.96853 X 10~3A33 -2.90769 X 10~sB2 -1. 18752 X 10-2B3 1.73129 X 10-*

55

NP Q

f START J

Lbl 05CALCULATE

Q

INPUTPA. OAT

NO

£Lbl 06

CALCULATE

Q @ 1000'

NO

Lbl 09

CALCULATE

Q @ SEA LVL

INTERPOLATE

CALCULATE

Q @ SEA LVL

OUTPUT

Q

C STOP J

56

ei LSI "HP 6

62 "PP ? "

63 46

94I1T.-. .-,

85 hFT-

86 41

87 XTOh

88 PROHPT

89 1 E3

19 /

11 STO 61

12 "OfiT ? "

1

1

48

14 XTOS

15 "PC*

18 41

17 =103

13f, i-. -^w r~. t-

19 STO 65

28 XEQ 61

21 ! in V

wL TONE 6

"8= "

C1 fiRCL X"iC

"h ^"

25 PROMPT

Li FIX 4

''-'A STOP

29 GTO 'HP 6

304'LBL 61

71 PCI 85J -

6.868"7*7

XEQ 67

34 RCL 81

JJ 1

7,h X<=Y?

.'if GTO 6570 "

i

39 RCL 85

46 W- *"

41 GTO 85

42 RCL 61

43 STO 86

1

45 STO 81

46 2,664

47 XEQ 67

43 XEQ 86

49 STO 16

38 PCL 65

si "10

Kt I.' \ '_'

ft/T"-

C7GTO 89

c.4j- RCL 85cr __ *v?~:~?

56 *

115CO

t

59*LBL 16

66 RCL X

61 RCL 16

62 -

r —

i

6 j RCL 88

64 *

••c00 -

66 RTH

67'HBL 65

68 RCL 81

69 2.884

76 XEQ 67

71+LBL 66"7-"\

1 L PCL 61

77i -J J, 1 i'-iCi

74 *

111, 627.- u +

f i' RCL 65

1 '_' -.797967

79 #

86 t

RCL 64

0£ RCl 863700 *

0^ .847954 E-6

00 *

86 +

87 RCL 83

88 -.61 44287i~ i~i

07 *

96 +

91 RCL 83

92 RCL 67

93 *

94 Cvi2248 E-<

95 #

96 +

v ! RCL 6200 ^I^f-

:"C: .J ._.

99 *

186 t

161 PCL 82

182 RCL 85

183 *

184 1.6 1889

185 t

166 t

187 RCL 82

188 RCL 86

169 *

118 _7•J 2345 E-4

111 *

112 +

113 RCL 82

114 RCL 67

115 *

116 3896 E-5

117 *

118 +

119 RCL 81

129 RCL 66

121 *

122 2.9 6853 F-3

123 *

+

ItJ RCL 81

126 RCL 87

l£.i *

128 _0 I

w t ?876 (

? E-5

129 *

138 +

131 RCL 96

132 -.91187!r-J

* 77I 00 *

134 +

135 PCL 67

136 1.7;J129 E-4

137 *

1 701 vj'.- +

139 RTH

148+LBL 87

141 STO 69

142 XOi

143 RCL X

144 RCL x

145 V+7

146*LBL 83

147 i U IHD 69

143 *

149 ISG 89

156 GTO 83

57

1 J-J

15*

151 PIN

152*LBL 99

153 PCL 65

154 -.6563

*

119,5

157 +

155 GTO 18

159 .END.

58

J. TORQUE TO HOVER IH GROUND EFFECT

Program Title: IGE

Accuracy: ±1% Q

Upper Chart


A = DA/1000

B = GWT/1000

Relationship: Regression eguation with BL as the depen-

dent variable.

Term Coefficient

Intercept -10.3038A .212035B .751590A*B3 . 160505 X 10-7A^ -6.61526 X 10-*A2B* . 165210 X 10-6AB3 -1. 90443 X 10"*AB* . 993143 X 1 0~

s

B« 1.21211 X 10-s

Lower Chart


A = Wind

B = BL

Relationship: Regression eguation with Q as the depen-

dent variable.

Term Coefficient

Intercept 50.2504B 4.97996A* 5.72239 X 1 0"

s

A«B3 .548313 X 10" 7

A*B* -.193279 X 10~aA3 -2.29042 X 1

0~

3

A3B2 -2.03324 X 1 0~ s

A2B2 1.96829 X 10"*

59

IGE

( START J

1

CALCULATEBL

ICALCULATE

Q

If RETURN

J

HIGE Q STORED R3]

60

81+lBl "IGE'

82 RCL 16

83 , £ 1 2S3?

84 *

83 -18.3833

Oi j= < cc'i c

8b x

87 UPS 89

88 7511 1 J J . J ?

89 *

19 X

11 RCL

12 4

171 J YtX

11 RCL.-.-»

< ri J #

16 .16?;595 E-7

17 ±

18 4.

1? RCL 07i. :

28 -d.ii!52;£ E-4

CI

K L L i >J

RCi 24

53 t

•r

55 f r

'

88

56 7

C7 v*yJ ;

i i :\

RCL -Q

59 *

68 5/4071 7L.

61 ±

h/ +

63 RCL 88

64.1

4

65 y * ''

66 RCL 29

67 *

681 r>3279 [

69 *

79 i.

71 RCL 11

TJ yI £ j

l'_*

74 _0 '.

C 1 i!9942 E

i' J *

t. c -. • r RCL 11

UAO

o^ RtL 89

-1.99443 E-4

" u77'",J <~ c

7k RCL 18

ji RCL 24n.-.

*

39 .993143r c

48 *

41x

42

43 { j 1 ! 1 C_5L. -J

i .4

*

45 +

4h STO wi7

4.97996AG10 *

49 58.2584

59 4.

RCL 88

94

.'.i il

*

1.96829 Z-4

if.

+

810 31

EFB

61

K. TOBQUE TO HOVER OCT OF GROUND EFFECT

Program Title: OGE

Accuracy: ±1% Q

Upper Chart


A = DA/1000

B = GWT/1000

Relationship: Regression equation with BL as the depen-

dent variable.

Term Coefficient

Intercept 4.2954 1

A -7.98310 X 10-2B -1.29853A«B* .765896 X 10~«A2B* ,225432 X 10-6AB* .392898 X 10"*B2 7.75365 X 10-2

Lower Chart


A = Wind

B = BL

Relationship: Regression equation with Q as the depen-

dent variable.

Term Coefficient

Intercept 54.9889A -.152276B 5.00758A«B2 -. 137789 X 10"«A2 -1.70953 X 10-2A2B2 1.06374 X 10~*A3 -1.23812 X 10-2

62

OGE

C START J

CALCULATEBL

ICALCULATE

Q

If RETURN J

HOGE Q STORED R32

63

81*LBL "OG C

82 RCL IS

63 -7.9831 E-•2

54 *

65 4.29541

66 t

67 RCL 69

68 -1.2985:*

69 *

16 +

11 RCL 16

12 4

13 YfX

14 RCL 24

15 *

16 .765696 E"-Q

17 *

18 +

19 RCL 16

2% *'*?

i_ a ~: -.- 1_ ^ T'"

:

T' 3

23 .225432 F-h

24 *

25

26 RCL 16

27 RCL 24

'*:Q 39 *-'!*- 98 F-.c

36 *

31 r

32 RCL 22

33 7.75365 F-.•J

34 *

35 +

36 5TO 88

38 *

39 54.9889

46 t

41 RCL 11

42 -.152276

43 *

44 t

45 RCL 29

46 RCL 68

;i +

C5 RCL 28

53 -1.76953 : E-c

j *

+

56 RCL 88

57 y*9

CORCL 28

59 *

68 i.e<>374 E-4

61 *

62 *

63 RCL 1

1

64 RCL 66

55 *

66 -1 27915 ' E-.- -i

bv *

cG +

69 STQ 70

76 .ENS.

49

56

778S E-6

64

I. MAXIMUM EANGE - TWO EHGINES

Program Title: RNG

Accuracy: ±1% KIAS, ±.00 1 NM/IB

Independent Variables (all three charts) :

A = GWT/1000

B = PA/1000

Upper Chart (This chart was not programmed.)

Relationships:

For PA = sea level GtfT < 18,000

Q = 34.047755 A-262953

For PA = sea level GWT > 18,000

Q = 27.175861 [4.984697 X 10 7 ]**A-i

For PA = 2000 GWT < 17,000

Q = -11.2467 In (A) - 29597407 A" 6 + .178 X 10-«A8 + 100.6

For PA = 2000 GWT > 17,000

Q = 649.485192 A~ -7«a*ii

For PA = 4000

Q = -2.9459 A - .56081 X 10*A- 7 + -15477 X lO-'A* + 110.325

For PA = 6000

Q = -.151820 A2 - 3402987 A~s + .635606 X 10~* A* + 96.4384

For PA = 8000

Q = -.227207 A2 - 4646405 A~s + .146173 X 10~a A a + 107.055

For PA =10,000

Q = -79.9623 A**A"* + .803736 X 10* A" 7 + 138.181

65

Middle Chart

Relationships;

For PA = sea level GSJT > 18,000

CAS = [4.16747 X 10~5(A - 14-1227)2 + 7.11631 X 10-3]-*

For PA = sea level GWT < 18,000

CAS = [7.19502 X 10-*(A - 13.4511)2 + 7.60263 X 10~3]-»

Remainder of chart is regression equation with CAS as the

dependent variable.

Term Coefficient

Intercept 86.8528A 4.55657A* -4.02861 X 10-*A*B 1.18176 X 10-*A3B -2.64073 X 10"3A2B2 -6.85829 X 10~3AB2 .103665AB« 5.71337 X 10"*B« -9.58130 X 10-3

lower Chart

Relationship: Regression equation with Onit Range as

the dependent variable.

Term Coefficient

Intercept .117152B

r -8.62852 X 10"3A*B -.577580 X 10"?A*B3 -.108601 X 10-sA2 -5.26033 X 1 0~

s

A2B2 -.648423 X 10"*A2B3 .412269 X 10~*A3 9.71483 X 10"*AB« -.162898 X 10"*

66

RNG

Lbl 05CALCULATE

CAS

NO

ICALCULATE

CAS SEA LVLj

Lbl 09CALCULATE

IAS

'

1

CALCULATEUNIT RANGE

1

f RETURN J

NO

Lbl 05

CALCULATECAS 2000'

INTERPOLATE

YES

CALCULATECAS I? SEA LVL

MAXIMUM RANGE:

IAS STORED R34

UNIT RANGE STORED F

35

67

01

1

LBL "RN!";

RCL 88

84 K<Y

85 GIG 83

8c cr 63

87<LBL 85

88 RCL

89 RCL 88

18 *

1

1

i.H5176 E-4101 C *

17. 36, ~:.J £ \t

14 t

4 C KM 1J

lb -4.132861 ! E-4

17i

:

?•

18 +

19 PCL 88

28 4.5'5657

21 *

?v +

ft-? an 07b--.1 r.LL C--'

-.J.11 PCL 88

i;

26 -2.i

07w !

*

00 +

i~ J PCL 00

38 RCL i

"3 <i-

70 ~6.

'

55829 E-3j. * *

1 •* +

TT pi"! 89"i .-

PCL 10i >-'

77 *

38 .1h: thhS

*

48 X

41 RCL 89

42 20

43j 4 c 7

•J . i

1 777 E-4

4"' *

46 t

47 PCL 29J AHO -9 <r ft « 7

.'0 ! •- E-3

49 *

56 +

51H i* ft ^ * ^

c--. GTQ 89

5.7 STO 34

54 PTH

55*LBL 63c.c C T fi 'j £

K7•J I

i 1 / \ ./

eftSTO 68

59 KEQ 66

68 XEQ 85

6! 18

PCL 89

63 n'<=Y?

64 GIG 64

65 -14.1227

t

67U11

• ft

68 4.16747 E

69 *

78 7.11631 E

71! i +

! L J A

|0 iji U 8?

74*L8L 64

75 -13.451:

76 +

i

i

77 V*?

78 7.1^562 E

79 *

88 7.68263 c

81 +

ft ft { lVOi. i ' ft

83+LBL 67

84 ENTERt

85 ENTERt

86 RCL 86

87 STO 63

38 ENTERt

84 KE8 66

98 RDN

r i c

92 /

93 KOY94 PCL 34

Q=; -

96 *

97 CHS

93 +

99*L8L 89

188 1.83531

181 *

182 5.538687

183 -

184 STO 34

185 GTO 88

18S*L8L 86

187 Xt2

183 STO 184 ft.u y+ft

118 STO 28

111 RTH

!12*LBL 88

113 RCL 68

114 -8.62852 E-3

!15 *

116 .117152

117 +

113 RCL 24

119 RCL 83

128 *

101 _ S?7=;0 r_7lwi . J I

-•- C i

4 ft ft

ICC *

107 +

124 RCL 24

125 RCL 19

*

107 -.1!53681 E-.0

123 *

129 +

138 RCL ??

131C '

J. 156833r c

".J

1 70 *

133 +

134 RCL ?o

135 RCL 13J. -J

1 -ib *

137 -.648423 E-6

138 *

139 +

148 RCL 00Ll.

141 RCLi ft17

142 *

143 .4i:5269 c.

144 *

4 iC+

146 RCL 89

147 RCL 68

148 *

149 9.7 1483 E--4

158 *

68

151 +

152 RlL fc'7

!53 RCL 28i -_'--

154 *

i v J -.162393 r

4 r- .-

1 -JO *|rn1 5

:" +

« c." C T i*i IK.- T '.- •.»-_f

iC;j ntui-.w p 1

M

166 .END.

69

M- HAXIHOH ENDORANCE - TWO ENGINES

Program Title: ENDR

Accuracy: ±1 KIAS, ±10 L3/HR (valid only for PA < 6000)

Independent Variables (all three charts)

:

A = GWT/1000

B = PA/1000

Upper Chart


dent variable-

Coefficient

2.162472-346991.39390 X 10-*.341286 X 10-12

-.564025 X 10-n.572765 X 10-7

-.143151 X 10-s

Middle Chart

Relationships:

For PA = 6000 GWT > 20,750

CAS = -7.00 A + 214.25

Remainder of chart is regression equation with CAS as

the dependent variable.

Term Coefficient

Term

Interce PtAA^BA&B*ASB 6

A*BA5B

Intercept 38.5672A

*1.21284

A* 2.86275 X 10-sA^B 2 -2.73779 X 10-sA 6 B 6 -.474676 X 10-12A5B* . 168795 X 10-aA 6 B -.958807 X 10-7A*B2 -.470741 X 10-sASB .270604 X 10-sA-

2

217.383B-s -.496303

70

Bottom Chart

Relationship: Regression equation with

Fuel Consumption / 1 00 as the dependent variable

Term Coefficient

Intercept 6.19995A .103193B -.226709A«32 .780189 X 10~*A 4 B* .188099 X 10~ 8

A3 2.08597 X 10"*A3B3 -.773409 X 10~*A2B2 7.46164 X 1 0" s

B2 4.87393 X 10-3

Note: This program and curve/surface fits for all three

charts are only valid for PA < 6000.

71

ENDR

JLEL

Lbl 05

CALCULATECAS

CALCULATEIAS

CALCULATEFUEL

CONSUMPTION

C RETURNJ

CALCULATECAS § 6000'

ILbl 05

CALCULATECAS G> 4000'

IINTERPOLATE

MAX ENDURANCE:

IAS STORED R36

FUEL COMSUMPTION STORED R3;

72

91 +LBL "EHBR'

62 GTO 92

83*LBL 18

04 STO Uc

85 XOY96 EHTEPf

9? EKTERf

88 EHTERt

99 Kt2

18*LBL 11

ii STO IND 98

12 *

13 ISG 66

14 GTO 11

i -.' h i n

16*LBL 92

17 4

18 RCL 88

26 GTO 65

21 26.75

22 RCL 89

°5 so Z

28 STO 86

27 Rt

STO 6?

51H.BL 88

52 RCL 89

53 1.21284

cr 70 C,A72

38}

31

STO 65

77iiB.fhi i

34i«r.*.

16

35 STO 21

PCL 09

•J I

70 *

79 214,,25

40 T

41 aES 86

42 EHTi[Rt

43 HO 7

44 -

45 RCL 65*

47 -

inGTO 88

49 >LBL 65

56 +

PCL-1 J

eg2.8ii£l J E-5

59 *

68 +

6! RCL

62 RCL 18

63 *

64 -2,73: E-5. —65 ?

66 +

K ? RCL 26^ ,-

bo PCL L. I

69 *

78 -.474626 E-37'1 i t

f £ t

-j-j RCL

•ci

'.• Cw

74 RCL Vk

: J *

76 .168795 E-8">7I I

*

i'+

79 PCL 26

88 PCL 88

81 *

Oil -.95888? ' E-7

-I1 *

i"j .<

0*1 t

0-. PCL 26ft ." DPI < n00 K'jL iu

Of *

j>000 -.4'

1 «i t j E-8

oc ±

98 +

0.*

RCL"<

-"' * w*.'

9? RCL 68,-. -1

y -:*

94 .27i3664r c

95 *

96

Q7 PCL?••

.• 1 *•«

Tf. 1/K

99'»-.383

IBfi *

181 +

162 RCL 98

183 SQR1

184 -.4^'6383

195

166 t

187 FS? 93

188 GTO 88

189 RTN

118+LBL 88

111 1.8"1531

112 *;

113 5.5; 1

114 -

115 sTO 76

116 FC?i ; 83

117 GTO 99

118 GTO 83

119*LBL 69

128 PCL 66

121 STG 68

122 18.8211071 Cv KEQ 19

124 CTil<l- i

125+LBL 83

126 RCL 99

127 .183193

128 *

129 6.19995

139 +

131 RCL 88

132 -.226789

133 *

134 +

135 RCL 24

136 RCL 18

1771 Jl *

1 70lio j'ol3189 E-7

139 *

148 +

141 RCL

142 RCL 26

143 *

144 .18!5999 E-8

145 *

H6 +

147 RCL 23

148 2.8:P597 r-4

149 *

159 +

j« S> g3

73

151 PCL0*7

152 pr-i 19*•-. w

153 *

154 ", f f J•to 3 E-6

155 *

ic £

-t-» -••-•

1 -J 1 RCLy":

158 Pf!• Q

r- '-• i_ i

1S9 *

168 7.4*.164 E-5

161 *

•1 •• TiCil t

163 RCL 13

164 4.8/ 39 '5 t-i

165 *

166 +

167 169

168 *

4 .- .-. - -r - "^TIb9 S !

._: i"

176.CUT

74

N. ABILITY TO 8AISTAIN FLIGHT - ONE ENGINE

Program Title: ENVLP

Accuracy: ±1 KIAS (valid only for GWT > 15,875)


A = EA/1000

B = GWT/10 00

C = Q/10

Upper Chart

Relationship: Regression equation with BL as the depen-

dent variable.

Term Coefficient

Intercept 13.1709E 3.24579A*B* .384129 X 10-*A^B 1.69462 X 10~3A3B3 -2.75020 X 10~sA^B* .808802 X 10"«A233 2.41848 X 10-sB2 5.11714 X 10-2

Lower Chart

The influence lines were curve fit individually and are

identified as being above the baseline (Vmax) or below the

baseline (Vmin) and corresponding to a GWT influence line in

the upper chart. All the lower chart influence lines have

the form

KIAS = 10[ (a + c C + e C2 + g C 3 )/(1 + b C + d C2 + f c 3) ]

Vmax

GWT

14,000 205.106051 -3.172488 -52.767525 .13684216,000 15.366945 -.343431 6.089327 -.08025918,000 158.178056 -.195222 -23.152443 -.18163220,000 377.359873 -4.019234 -71.947887 .13029721,000 142040.814 -1559.5132 648.6062 -220.3889

75

GWT

14,00016,00018,00020,00021,000

-3-096207-3.234997-2.229709-2.795544-8747.8908

.047131

.014180

.021735

.02856736.399824 714

952305284553320453,639954013828

Vmin

GWT

14,16,18,20,21,

000 -561.,206728 -20.296937 -102.,617993 1. 262022000 • 269674 1.745743 -12.,269365 -.715187000 142. 721580 -.530094 -51.,367270 -. 101086000 637. 457451 3.703332 -133.

, 209123 -.453900000 208. 927822 -.861527 -51..818192 . 159518

GWT

14,000i6;ooo18,00020, 00021,000

48.2.5.9.4.

3083831403 45645454038421405128

259697061489017929006561008074

-3. 033215069948180476213390128383

Note: Although the curve fits for the entire figure are

accurate (except as noted on the figure itself) , the program

ENVLP is valid only for GWT > 15,875.

76

ENVLP

DETERMINEAPPROPRIATEINFLUENCELINES

ICALCULATE

LOWER VmaxVALUE

CALCULATEHIGHER V,

VALUEmax

IINTERPOLATE

If necessary

1OUTPUT

''max

CALCULATEHIGHER Vmm

VALUE

ICALCULATE

LOWER VminVALUE

IINTERPOLATE

If necessary

OUTPUT

Vmin

If STOP J

** Under certain conditions the

BL value lies outside the last

influence line. In these cases

Vmax an d Vm in are based solelyon the last influence line.

77

B1*LBL "EHVLP'

62 8

63 XOF64 FIX 8

65 "Bfi ?"

8b 48

87 XTOfi

88 "!-FT"

69 41

18 XTOP

11 PROMPT

12 1996

13 /

14 STO 18

15 3

16 YtX

17 STO 27

IS "GMT ?

19 49

28 XTOfi

21 "KB"

22 41

23 XTOfi

24 PROMPT

Km \.* 1 *J O '.'

*--

27 STO 89

28 22,624

29 XEQ 67

i 8 t •'

31 46

32 XTOfi

34 41-T 1 : T ,-, --.

•J — : i ' 'Jn

36 PROHFT

37 STO 38

33 GTO 81

39*LBL 67

48 STO 86

41 KO'f

42 EHTERt

43 EHTERt

44 Xt2

45+LBL 08

46 STO IHD OO

47 *

48 ISG 60

49 GTO 03

56 RTH

5ULBL 61

52 RCL 69

53 3.24579

54 *

55 13,1789

56 +

57 RCL 18

58 4

C Q v + V•J 7 ITA

t'h RCL 24

61 *

62 .384129 E-"f

63 *

64

65 RCL 27

66 RCL 89

67 *

63 1,69462 E-^

-.',

69 *

79 +

71 RCL 27

72 RCL 23

73 *

74 -2.7502 E-r

7C, t

76 t

77 RlL 277C p^! •-, .«

79 *

88 .388882r_6

07 RCL 16

V*"'

r.c03 KlL 2j

86 *

r-.f

Of« | 4 n i o j- ci.'tlsto t j

83 *

89 +

r«-- Dpi t'O

7*1

91 5 Ii?l4 F-?vi 111 il L. t_

92 *

97 +

94 16

95 /

96 STO 14

Q? RCL X

QO70 LH

99 -19.56

188 ¥

191 52.'415

182 +

183 RCL 18

164 X>'f}

185 GTO 13

186 RCL L

187 RCL 38

188 18

169 /

118 STO 13

111 X<='<'

112 GTO 85

113 XE9

114 XEQ 28

115C1I

\

116 STO 87

117 889,,883

118 RCL 14

119 LBL 84

126 RCL 1KB Y

121 X>Y'}

122 GTO 15

107 SF 81

124 RDN

125 ISG Y

126 GTO 84

127 GTO 16

!23<LBL 15

129 FC?C 91

138 GTO 13

RCL 13

132 X<=\'7

177 XEQ 12

134 FC? 83

135 RDN

136 -

137 CHS

138 4

139 ST+ 7i.

148 RBN

141 RCL 1KB Y

142 /

143 STO 87

144 RBN

145 IS

146 +

1*1 STO 12

!4S<1BL 14

149 XEQ INB 1:

159 XEQ 29

78

151 XEQ "FIT"

152 FSv 03

153 XEQ 11

154 STO 14

155 1

156 ST- 12

157 KEO I NO 1

i ca urnijo sty 20

159 XEQ "FIT"

168 RCL 14

161-

162 RCL 87

163 *

164 RCL 14

165 +

166 IS

167 *

163 FS^ 92

169 GTO 83

178 XEU 82

171 FO? 83

172 GTO 13

173 RCL* 7* -j

174 STO 14

l- J Kl-L 48

176 STO

177+LBL i 7

178 6

179 ST+ 10

on PTfi105 lilUi A

18HLBL 18

182 6.875

183 Rt

1 '-• 1T

* oc: y / •..

14

186 GTO 69

187+LBL 11

183 RCL 17

189 STO 48

199 RCL; i

191 STO < 7i •3

17i KL-L7

• Q7 DTli

' ^tt - 11 12

185 *<>' I

196 RDM

197 -

193 CHS

199 EHTERt

206 Rf

261 +

282 STO 13

283 RCL 7

284 INT

285 X=8">

286 GTO 16

287<

i

288 -

289 RCL IHD X

2l9 Rt

211 +

1 X<> 14

017 v/ \vft : 1 1

214 j1

01 c+

216 XOi

217+LBL 89

iliO RCL INB Y

oi q SF 83

228 RTH

221+LBL 16-\ 1 1LLi. SF 84

007 Rt

224 -

OOC STO 14

226 mC.L. i XEQ 28

228 XEQ "FIT"

RCL 14

-

07*L.'l 18•"1 "^ "

*

233*LBL 8207-4 TOHE 6tic

"VHhX=

236 flRCL y

t: "?7"r £

Tn. 1

070d u PROHFT

239 FS? 64

248 IjilJ 17

241 SF 02si-*

RTH

243*LBL ci i

244 '' F o 36

245 XEQ 23

246 XEQa r T Tr i !

RCL 14

1 i.• H " +

251LBL 83

252 TOHE 8

253 "VHIH="

254 fiRCL X

255 "f- KT"

256 PROHPT

257 GTO 66

253+LBL 85

259 TOHE 8

268 "HO EHVLP"

261 PROHPT

262 GTO 86

263*LBL 13

264 TONE 8

265 "IMfiCCURHTE-

266 PROMPT

267H.BL 86

263 6

269 XGF278 FIX 4

271 STOP

272 GTO "EHVLP"077*1 pi 01

c ; t 1 . cj

1,875

276B"7C

t 'J i ••'

977LI l" XEQ 19

07068 16.45

279 8.875

288 00=:1 1 Oi .'

001t-01

7 -?cI . i J

RTH

283»LBL 22

284 ,2345^3

285 .81418

286 -3.234997

COi' XEQ 19

£00 -.888259

289 6.889327

298 -.34343100

1

c/i 15.366945

292 RTH

293*LBL 23

294 .328453

295 .821735

296 -2.229789

249 18

258 *

297 XE6 19

298 -.181632

299 -23.152448

388 -.195222

79

381 158.178856

382 RTH

383+LBL 24

384 .639954

385 .828567

386 -2.795544

387 KEQ 19

388 .138297

389 -71.947837

318 -4.819234

311 377.359373

312 RTH?)7ai oi OSJ i-.'*UUL i. J

71 4 7 < * Q\ 7000

315 36.399324

316 -8747.898735

317 XEQ 19

318 -228.3889

319 643.666162

329 -1559.51316

321 142848.8147 •:•:• DTu.-i-i. Kin

323+L8L 27

324 -.869948

325 .861489

326 2.148345

327 XEQ 19

323 -.715187

329 -12.269365

338 1.745743

331 .269674

332 RTH

333+LBL 28

334 -.188476

335 .81-7929

336 5.645454

337 KEG 19

338 -.181836

v.9 -51. 36727

348 -.538994

341 142.72158

342 RTN

343+LBL 29

344 -.21389-; ac

346 9.833421

347 XEQ 19

348 -.4539

349 -133.28912:

358 3.783332

DvOjO

i

351 637.457451

352 RTH

353+LBL 38

354 -.123883

355 -.898874

356 4.485123

357 XEQ 19

358 .159513

359 -51.8331927£u _ D£ 1 507

362 RTH

363*L8L 19

364 STO 84

365 RDH

360 STO 85

367 RDH

368 STO 66

369 RTH

378*LBL 28

371 STO 88

372 RDH

373 STO 81

374 RDH

375 STO 92

376 RDH^ ^ *

1 nt .-. ,-1 ^^' ' -'II T> '

378 RTN

379*L8L TIT"

388 RCL 13

701 7

333 EHTERt

384 EHTERt

335 RCL 86

336 *

W RCL 13

700 >*-•ju'.: n 1

1

389 RCL 84

396 *

391 +

392 RCL 13

393 RCL 82

394 *

395 t

396 RCL 66

397 +

398 RCL Y

399 RCL 65

498 *

461 RCL 13

482 Xt2

483 RCL 83

484 *

485 +

486 RCL 13

487 RCL 61

488 *

469 +

418 1

411 +

412 /

413 RTH

414 .END.

80

0. HAXIMOM RANGE - CHE ENGINE

Program Title: SE RNG

Accuracy: ±1 KIAS, ±.001 NM/LB (valid only for PA < 6000 )

Independent Variables (all three charts)

:

A = GWT/1000

B = PA/1000

C = GWT/10,000

Upper Chart (This chart was not programmed.)


dent variable.

Term Coefficient

Intercept 10 8.555B -2.90288B3 1-66076 X 10-2B* -1.41413 X 10-3

Middle Chart

Relationship: All influence lines are of the form

KCAS = [(a + cA + eA 2 +g A 3 )/(1 + b A + d A 2 + f A 3) ]

PA

S.L. 502.369992 .362933 -23.349262 .0052772000 17512562.0 -760. 134361 -3460915- 51 -420.6629814000 -225-872732 1.343442 237-964440 -. 1122376000 6009.210952 5.758043 316-015707 .2975258000 139.362855 19.800377 141 .568193 4.41705810000 371.074536 . 117628 -22.090544 -.000925

PA

S.L. 4.550521 --000784 -.1828462000 167590.8365 21.738883 -2020.2845894000 -19.841131 .002110 - 4238416000 -4.695139 -.032069 -1. 5461688000 -51.565799 -8.730509 -39.64460710000 .575690 -.000568 -.034429

81

Bottom Chart


UR = (a + c C + e C2 + g C3)/[10(1 +bC+dC2+f c 3 )]

PA

S.L. .925295 -1. 486832 -1. 178663 .8992702000 1384-426869 8105.,208102 9968.,662342 -7100.,2183824000 -212.048697 -125. 637807 227. 277663 158.,9553076000 -204.717059 -151.,075119 173.,057337 196.,8561378000 9.078675 -4. 835348 -25.

, 043409 2.,72160710000 67.098651 23.,295696 -8.,710976 20. 183821

PA

S.L. *.682470 •.194762 i , 15323020 -9863..619555 1539..514953 2283..6143064000 -28.,1 12 57 4 -48.,228909 -16.,3758746000 40.,296510 -61..780622 -39.,3300578000 17.,309474 a , 179344 -3..42575310000 10..733 73 1 -20..628002 -17.,839002

Note: Although the curve fits are accurate for PA < 10,000

on each of these three charts, the program SE RNG was

written and is valid only for PA < 6000.

82

SE RNG

C START J

DETERMINEAPPROPRIATEINFL. LINES

CALCULATEUPPER CAS

VALUE

ICALCULATELOWER CAS

VALUE

IINTERPOLATE

ICALCULATE

IAS

ICALCULATEUPPER U.R.

VALUE

ICALCULATELOWER U.R.

VALUE

INTERPOLATE

C RETURNJ

S/E MAX RANGE:

IAS STORED R40

UNIT RANGE STORED R41

83

8t*LBL -SE RHG

62 RCL 69

83 STO 13

64 2.89662

65 STQ 12

86+L6L 65

67 RCL 12

88 INT

69 RCL 68

18 X<=Y^

11 CIO 67

12 ISG 12

13 GIG 85

14 GTO 68

15*LBL 67

16-

i ft

i /

19,i *r /,

3 1 'J 14

28 XEQ IHD 12

XEQ 11

cc XEQ "FIT"07i. J

CTi"J u 46

A 4 iil

c3 j t 12

26 XEQ IHD i:

27 XEQ 11

28 XEQ "FIT-

29 RCL X

36 RCL 46

31-

32 RCL 14

7 •*

RCL 487C +

^_.-

1.8:

-!:

l" *

*-G^ C7•J t -J -If

7,Q -

46 •J 1 *-T 46

411 * GTO

4~+i l?i 68i7

999

44 STO 46J!T

STO 41

46DTLi

47*LBL 11

48 CTfi 68

49 RDH

56 STO 61

Ji Klin

52 STO 62

53 RDM

54 STO 83

-.'j r I ii

56*LBL 66

57 -.183

58 -7.84 E-4

59 4.55

69 XEQ 69

61 5.277 E-3C? _07 7C

63 .3629

64 592

65 RTH

66*LBL 62

67 -2629.3

68

Zd \f?c frob 7 1 'j 1 v C i.

76 XEQ 69

71 -426.66

72 -3461 E3

ii -f'bt'

.'4 i?ji2b t2

75 RTH

76tLBL 64

{( . 4ilio4

78 2.11 E-3

79 -19.84

88 XEQ 990! _ 11--.'.'1 i lii.

DO OTC

33 1.3434

84 -226

en n •?

j

: Ll.it

85 RTH

86+LBL 86

87 -1.546*

83 -.63207

39 -4.695

98 XE8 89

91 ,2975

92 316

7J !j, :

-

.jo

94 6669

95 RTH

96*LBL 13

97 16

93 ST/ 13

99 12

166 STt 12

181 XEQ IHD 12

182 XEQ 11

163 XEQ "FIT"

164 STO 41

165

166 ST- 12

187 XEQ IHD 12

183 XEQ 11

189 XEQ "FIT"

118 RCL 41

111 -

112 RCL 14

113 *

114 ST+ 41

115 38

116 ST/ 41

117 RTH

118*LBL 16

119 -.15323

128 -.1948

121 .6825

122 XEQ 89

123 .8993

124 -1 179

125 1 1 S'Ji

126 .92531071 Ci RTH

128<LBL 12

129 2233.614

138 1539.5

131 -9363.6

132 XEQ 89

133 -7186! 7 Jlit 9969

135 3185

136 1384.4

137 RTH

138+LBL 14

139 -16.376

149 -43.229

141 -23.113

H2 XEQ 89

143j en qcc1 J'J. ?jO

144 007 00

145 LC-J.ti 4

146 -212.85

147 RTH

148*LBL 16

149 -39.33

159 -61 .78

84

15! 48-2965

152 KEQ 09

153 196.356

154 173.357

i JJ I --• L = '.' i J

156 -294.717

157 RTH

15S*LBL 89

1 ="CJ CI U tf4

169 PDH

161 STO 65

162 RDM

163 STO 96

164 PTH

165 .END.

85

P. HAXIHOH ENDURANCE - ONE ENGINE

Program Title: SE ENDE

Accuracy: ±1 KIAS, ±10 LB/HP.


A = GWI/1000

B = PA/1000

C = GWT/10,000

Upper Chart


dent variable.

Term Coeffi c ient

Intercept -51.2108A 10.8546A*B3 -.104315 X 10-6A*B* .851402 X 10~8A2 -.167166A2B2 1.10126 X 10"*AB -1.96415 X 10-3B* -1.12832 X 10-*

Middle Chart

Relationship: Regression equation with CAS as the

dependent variable.

Term Coefficient

Interce pt 83.4630AB3 -1.56384 X 10-*A* .895430 X 10-7A*E -.221193 X 10-8A3* .720428 X 10-7A-

2

-2818.02B^B-1 -8.27505

86

Bottom Chart


Fuel Consumption = 1000[a exp (b C) + c exp (d C) ]

PA a b c d

S.L. .767279 .434063 -.418050 .4490002000 3.671098 .378791 -3.357889 .3698554000 .947504 .501061 -.658054 .5001616000 -31.000000 -270.000000 .252300 .5801248000 -31.327759 -269.600916 .236572 .61128410000 .835295 .916064 -.678990 .922650

87

SE ENDR

C START J

DETERMINEAPPROPRIATEINFL. LINES

CALCULATECAS

CALCULATEIAS

CALCULATEUPPER FUELCNSMPTN VAL.

CALCULATELOWER FUEL

CNSMPTN VAL.

S/E MAX ENDURANCE:IAS STORED R42

FUEL CONSUMPTION STORED R43

INTERPOLATE

C RETURN )

88

6ULBL -St EHDR

92 2.81662

93 SIC 96

Hi. RCL 68

65LBL I -J

96 RCL 86

67 I HI

63 X>Y 1

69 GTO 85

18 RDH

11 SF iBl

12 ISG 86

13 GTO< cI -J

14 Rt

15 STO 86

16 t! Rl 851 7 -

18 C

15 /

26 STO 97

23 FC?Ij 81

22 GTO 87"'7

1LBL 18

24 RCL 69

25 RCL 19

26 *

CI -1.56:

Opi-'- 1 *

83.463

38 +

31 RCL 26

.39^543 E-7

33 *

34 t

35 RCL 26-* .-

it. RCL 9377 *

70•JV -.2:•1 193 E-S

39 *

49 +

41 RCL 69

42 RCL 01L. 1

43 *

44 .729428 E-7

45 *

46 t

47 RCL

48 l-'X

49 -231 8.82

56 *

51 +

52 RCL 88

53 RCL 68

54 J/Xcc

, V+'-'

C£ _0 07TQC;

58 +

59 FS?C 82

69 RTN

61+L8L 99

62 1.83581

63 *

64 5.53

65 -

66 STO 42

67 GTO 31

68*LSL 83

69 STO 83

78 3

71 YtX

72 STO 19

73 Xt2

74 STO 21

75 RTN

76*LBL 67

77 SE 62

73 RCL 88

79 STO 14

Oflob d

8! XEQ 83

32 XEQ 13

83 RCL X

84 RCL 89

35 .8341

86 *

87 EtX

83 35.9739

89 *

98 -

91 RCL 67

93

94 RCL 14

95 XEQ 83

96 RUN

97 GTO 69

93+LBL 11

99 XEQ IHD 66

188 XEQ 13

181 XEQ 14

182 STO 85

163 2

164 ST- 86

185 XEQ IHD 86

186 Y£Q 1 71 -'

187 XEQ 14

183 RCL 85

189 -

118 RCL 97

111 *

112 RCL 85

113 -

114 1 E3

115 *

116 CHS

117 STO 43

118 RTN

119*L8L 13

128 STO 83

121 RDH

122 STO 92

123 RDH

124 STO 81

125 RDH

126 STO 68

127 RTH

128»LBL 14

329 RCL 81

138 RCL 89

131 18

132 /

1 77 'NT '" 10

134 *

135 EtX

136 RCL 68

137 *

133 PCL 83

139 PCL 12

148 *

341 EtX

142 RCL 92

143 *

144 +

145 RTH

146*LBL 86

147 .767279

143 .434863

149 -.4! L/C'

J

158 .449

89

151 RTN

15MBL 62

1 JO 3.671993

154 -77^701

i j j

i ^cTfn ft ft

-3.35738?i c - .369355* -"-'

1 571 J

:' RTH1 c-iii r.i n a

159 .947504

168 .581661

161 -.653654

162 .586161

163 RTN

164*LBL 66

i f~> -31

166 -278

167 .2523

163

169 RTN

179+LBL 6?j ^ j 7( 7 <J77ca111

1 1 L -269.6

1 ? i*5 7 £ S 7 'J

L. J 'J _• i £_

174 .6112841 -7Ci i -j PXH

176*LEL

11'

F

07C-!<jC

1 7-Q .916864

179 -.67899

1 QS .922654 "i *

i u 4 RTH

182 .LHB.

90

Q. GBOOBD ROLL - POWER OFF

Program Title: ROLL

Accuracy: ±10 FT

Upper Left Chart

This chart is a modified version of the Density Altitude

chart. The relationships developed for the Density Altitude

chart are valid for this chart, also.

Upper Right Chart


A = DA/1000

B = GWT/1000

Relationship: Regression equation with 3L as the depen-

dent variable.

Term Coefficient

Intercept 6.25495A .130801AB« . 364592 X 10"*B* -1.47043 X 10-sA* . 142700 X 10-6B* .279130 X 10-7B-i -67. 1310

Lower Chart


A = Wind

B = BL

Relationship: Regression equation with Ground Roll

Distance as the dependent variable.

Term Coefficient

Intercept 1.49721A -.121041B .500958A* -.839100 X 10-6A2 2.01268 X 10-3

9 1

ROLL

( START \

I

—

InputDA, GWT, WIND

V

CALCULATEBL

\

CALCULATEGROUND ROLL

1r stop ^

92

61*LEL 8!

62 "Bh ?"

83 48A 1 V T "i "i

84 ft i Oh

05 "hFT"

86 41

97 XTOfi

es PROMPT

89 1889

18

ii STO 18

10 .pyr ^i — «-k i

13 48

14 XTOfi

15 KB"41

i i XTOfi

18 PROMPT

19 1888

28 /

01 STO 89y~.

4

07 y+vL.--' i 1 ft

24 STO 24OC

RCL 89

laV Vf?

07 *

•~ 1*1

STO 26

29 WIHB ?

38 46

31 XTOfi

j -JL. i r- !

•J-1 41

34 KTOfl

35 PROMPT-1 ^

STO ii

37 r.t £

70 CTfl 00

V--U A

1

ftT£

46 STO 29

41 XE9 62

42 FIX 8

TONE 8

44 KulL-

45 hRCL a

46 "Y FT: '

If PROHPT

to FIX 4

49 RTH

56*LBL "ROLL

51 GTO 61

52*LBL 82

53 RCL 16

54 .136381

55 *

56 6.25495

57 +

53 RCL 18

59 RCL 24

68 *

61 .364592 E-6

62 *

63 +

64 RCL 24

65 -1.47643 E-5

66 *

67 +

68 RCL 18

69 6

78 YtX

71 .1427 E-6

72 *

73 +

74 RCL 26

75 .27913 E-7

76 *

ii +

78 RCL 69

79 1/X

88 -67.131

31 *

32 +

83 .586953

34 *

OC 1 iQ70|

86 *

87 RCL 11

88 -.121841

39 *

98 +

91 RCL 29

92 -.8391 E-6

93 *

94 +

95 RCL 28

96 2.61263 E-3

97 *

98 *

99 188

188 *

181 RTN

182 .END.

93

E. MASTEE PBOGEAM

Program Title: FLIGHT

Accuracy: (not applicable)

Purpose: This program resides in main memory and controls

the input, execution, and output of the following programs

(residing in extended memory) :

DA

E PEEF

IGE

OGE

STALL

ENG

ENDE

WTE T/0

SE ENG

SE ENDE

PEINT

Additionally, through subroutine A (Preflight Planning) and

a subordinate program PRINT, this program (FLIGHT) will

execute all of the programs listed above in succession, and

if a printer is attached, produce a printed output of the

results. The subroutines included in this program are:

Subroutine Corresponding Program

A PP

a DA

B E PEEF

C IGE

C OGE

D STALL

E ENG

e ENDE

94

F

G

H

01

02

03

04

05

06

07

FILL

FIT

WTR T/O

SE RNG

SE ENDE

Input OAT

Input PA

Input GWT

Input "Wind

Input DA

Input Fuel

Clear flags, Fix

Load required registers

Perform function:

a + cX+eX 2 + gX31+bX*dX2 + fX3

95

FLIGHT

C START J

SIZEMEMORYTO 044

GO TO'USER MODE'

I'SET DISPLAY

1Lbl 07

CLEAR FLAGSFIX

VXEQ DESIRED/

^SUBROUTINE

96

FLIGHT Subroutine A

f START ^

rTNPUT OAT,

PA, GWT, WINEi '

\

EXECUTEENDR

EXECUTEDA

1

1

EXECUTEWTR T/O

EXECUTEE PERF

1

1f

EXECUTESE RNG

EXECUTEIGE

i'

\EXECUTESE ENDR

EXECUTEOGE

\

\EXECUTEPRINT

EXECUTESTALL

>'

\C RETURN J

EXECUTERNG

97

FLIGHT Subroutines a,B,C,c,D,E,e,F,G,H

INPUTVARIABLES

IEXECUTEDESIREDPROGRAM

OUTPUTCALCULATED)'PARAMETERS)

If RETURN J

ALL OF THE NAMED SUBROUTINES HAVE IDENTICAL LOGIC FLOW. ONLY THE INPUTVARIABLES, CALLED PROGRAMS, AND OUTPUT PARAMETERS VARY AS SHOWN IN THETABLE BELOW.

SubroutineProgramCalled Input Output

a DA PA, OAT DA, CNV F

B E PERF PA, OAT Q

C IGE DA, GWT, WIND HIGE Q

c OGE DA, GWT, WIND HOGE Q

D STALL PA, OAT, Nr, GWT, AOB STALL IAS

E RNG GWT, PA, FUEL MAX RNG IAS & DIST

e ENDR GWT, PA, FUEL MAX ENDR IAS & TIME

F WTR T/O OAT, GWT WTR T/O IAS

G SE RNG GWT, PA, FUEL SE MAX RNG IAS & DIST

H SE ENDR GWT, PA, FUEL SE MAX ENDR IAS & TIME

98

enLBL "FLIGHT1

62 44

83 PSIZE

84 •J I C J

85 or 07A i.i

8t>LBL 6?

87 8

88 XOF89 FIX 8

18 "READY"

11 PROMPT

p FIX 4

13 RTH

14<1BL S

15 flBV

16 XEQ 81

17 ROV1011' XEQ 82

19 fiBV

28 XEQ 83

21 ftBV

£t XEQ 84

£j "Bfl"

24 GETF•-cL.-J XEQ "Bfl"

26 RCL 18

di'j•J

90CO YtX

29 STO 27

38 "E PERF"

33 GETP

32 XEQ "E PERF

"IGE"

34 GETP

J J XEQ "IGE"

36 OGE"77 GETP

38 XEQ "OGE"

39 "STALL"

48 GETP

41 188

42 STO 86

43 6

44 STO 81

45 XEQ "STALL"

46 RHG"

47 GETP

48 XEQ "RHG"

49 "EHDR"

58 GETP

51 XEQ "EHDR-

52 "HTR T/0"^7JO GETP

54 XEQ "WTR T/0ccJ J "SE RHG"

56 GETPC7J; XEQ "SE RHG"

58 -SE EHDR"

59 GETP

68 XEQ "SE EHDR

61 "PRINT"

62 GETP

63 BEEP

64 FS? 21

65 XEQ "PRINT-

66 GTO 87

67+LBL a

68 XEQ 82

69 XEQ 81

78 "DA"

71 GETP

72 XEQ "Dfi"

73 1 E3

74 *

75 TOHE 8

76 "BA=*

77 flRCL X

78 •V FT"

79 PROMPT

88 FIX 3

81 RCL 80

82 SQRT

83 1/X

84 CNV F='

85 flRCL X

86 PROMPT

87 GTO 87

38'LBL B

89 XEQ 82

98 XEQ 81

91 •E PERF"

92 GETP

93 XEQ "E PERF"

94 TOHE 6

95 "9=

96 flRCL 33

97 "F '/."

98 PROMPT

99 GTO 87

188 LBL C

181 XEQ 85

182 XEQ 83

183 XEQ 84

184 "IGE"

185 GETP

186 XEQ "IGE"

167 TOHE 8

188 "IGE Q="

189 flRCL 31

lie "F':•

111 PROMPT

112 GTO 87

113+LBL c

114 XEQ 85

115 XEQ 63

116 XEQ 84

117 -OGE"

118 GETP

119 XEQ "OGE-

128 TOHE 8

121 "OGE Q='

122 flRCL 32

123 "F V124 PROMPT

125 GTO 87

126*LBL E

127 XEQ 83

128 XEQ 82

129 "RHG"

138 GET?

131 XEQ "RHG'

132 TOHE 8

133 "IflS="

134 flRCL 34

135 "F KT"

136 PROMPT

iOf =EQ 86

138 RCL 35

139 *

140 TOHE 8

141 "RHG="

142 flRCL X

143 "F HM"

144 PROMPT

145 GTO 07

146*LBL e

147 XEQ 83

148 XEQ 82

149 "EHDR"

158 GETP

99

151 XEQ -EHDR"

152 TONE 8

153 IfiS=•

154 flfiCL 36

155 "1- KT"

156 PROHPT

157 XEQ 86

15S RCL 37

159 1/X

168 *

161 FIX 1

162 TONE 8

163 °EHDR='

164 fiRCL X

165 !- HR"

166 PROHPT4 f "*

167 GTO 87

168<LBL D

169 XEQ 82

178 XEQ 81

171 "HR ?

172 48

173 XTOfi

174 •K;-

175 41

176 XTOfi

177 PROHPT

178 STO 88

179 XEQ 83

188 "iBfiNK?'

131 48

182 XTOfi

183 "FDEG"

184 41 •

185 XTOH

136 PROHPT10?l'-'l STO 81

188 "STALL"

189 GETP

198 XEQ "STALL

191 TONE 8

192 IfiS="

193 flRCL 33

194 h KT"

195 PROHPT

196 GTO 87

1974>LEL F

193 XEQ 81

199 XEQ 83

268 WTR T/0-

281 GETP

282 XEQ -WTR T/0'

283 TONE 8

284 "IflS="

285 flRCL 39

286 "F KT"

287 PROHPT

288 GTO 87

289»LBL G

218 XEQ 83

211 XEQ 82

212 -SE RNG-

213 GETP

214 XEQ "SE RNG"

215 TONE 8

216 "IflS=-

217 flRCL 48

218 -F KT"

219 PROHPT

229 XEQ 86

221 RCL 41

222 *

223 TONE 8

224 -RNG="

225 flRCL X

226 "F NH"

227 PROHPT

223 GTO 87

229*LBL H

238 XEQ 83

231 XEQ 82

232 "SE ENDR-

233 GETP

234 XEQ "SE EHDR*

235 TONE 6

236 TflS=

237 flRCL 42

233 -F KT-

239 PROHPT

248 XEQ 86

241 RCL 43

242 1/X

243 *

244 FIX 1

245 TONE

246 -ENDR="

247 flRCL X

243 "F HR"

249 PROHPT

258 GTO 87

100

251*LBL 8!

252 OAT ? "

253 48

254 XTOfi

255 FC-256 411C7

XTOfi

253 PROHPT

259 STO 38

268 15.817

261 XEQ "FILL"

262 RTN

263<LBL 82

264 "PA ?"

265 48

266 XTOfi

FFT-

268 41

269 XTOfi

PROHPT071<. i 1 1 E3111etc /

273 sto es

274 18.82

275 XEQ -FILL'

276 STO 21

277 RTN

27S*LBL 83

279 •GUT ?"

288 48

231 XTOfi

232 "FLB"

°83— 'JV1 41

00AL'JT XTOfi

COJ PROHPT00CCOO 1 E3537COl /

288 STO 89

289 22.826

298 XEQ -FILL"

291 RTH

292 <LBL 84

293 "HIND ?"

294 48

295 XTOfi

296 "FKT"0Q7L. 7l 41

OQOt-7'j XTOfi

2<W PROHPT

368 STO 11

361 Kid

382 STO 23

383 Xt2

384 STO 29

•Jv -J RTH

386

1

LBL 85

387 'DA ?

38S 48

399 STOfi

318 •hFT"

311 41

312 XTOfl

313 PROMPT

314 1 E3

315 /

316 STO 18

717C'l i

7J

318 Yts

319 STO 27

328 RTH

32ULBL 867--V" FUEL ?

jL-j 48

324 XTOS

325 KB"326 41

327 XTOfl

7 ?fi PROMPT7VMW T— - RTH

338<H.BL "FILL"

331 STO 5277"* XOY333 RCL X

334 RCL X

335nri \i

336 xt2

337+LBL 18

STO INK 12

339 *

348 ISO 12

341 GTO 18

342 RTH

343-L8L "FIT"

344 RCL 13

345 7

346 m347 RCL X

34S RCL 96

349 *

358 RCL 13

351 Xt2

352 RCL 84

7=: 7 *

354 +

7CC RCL 13

356 RCL 82

357 #

358 +

359 RCL 88

368 +

361 RCL i

j62 RCL 85

3b3 *

364 RCL 13

365

j66 RCL 83

367 *

368 +

369 RCL 13

378 RCL 81

371 *

770•J ! L. +

j/

3

1

374 +

iij ./•

376 EHB

101

S. PBJHT PROGHAH

Program Title: PRINT

Accuracy: (not applicable)

Purpose: This program resides in extended memory and is

called by subroutine A to print a hard copy of the output

parameters stored in Registers 10 and 31 - 43.

102

PRINT

C START J

PRINT

^CALCULATED

j

PARAMETERS

C RETURN J

103

8ULBL "PRINT" 51 flDV

82 flBV

83 flDV

84 RCL 18

65 1 E3

86 *

87 "BA

83 ARCL X

89...

FT.

18 PRfl

1! flBV

12 31.849

13 HIGE Q '

14 XEQ 88

15 i- i-

16 PRfl

17 "H05E Q *

18 XEQ 88

19 I- ":•

28 PRfl

21 "BLftDE STALL

22 XEQ 88

Ci "P KT"

24 PRfl

flBV

26 flDV

"HAX RHG"00

PRfl

29 IflS

38 XEQ 8?

31 "P KTC

70•JL. PRfl

33 FIX 3"7 Jas UNIT RHG7CJ -J XEQ '88

36 "h HH-LB-

PRfl

j8 flBV

39 flBV

48 "HAX EHBR-

41 PRfl

42 FIX 8

43 IflS•

44 XEQ 88

45 •P KT"

46 PRfl

47 - BURN"

48 XEQ 88

49 P LB'HR"

58 PRfl

52 flBV

CIflBV

54 flBV

55 "S/E PERFORMANCE

56 PRfl

57 Q flVL"

58 XEQ 88

59 P >;

68 PRfl

61 " WTR T/0

62 XEQ 88

63 "P KT-

64 PRfl

65 flBV

66 S/E HAX RHG"

67 PRfl

68 " IflS

69 XEQ 88

78 P KT"

7i PRfl

72 FIX 3

77i •-' UNIT RNG

'

74 XEQ 88

75 -P HH/LB-

PRfl

77 flBV

78 • S/E HAX EHBR"

79 PRfl

88 FIX 8

81 " IflS

82 XEQ 88

83 "P KT"

84 PRfl

85 • BURN"

86 XEQ 8807a "P LB/HR"

88 PRfl

89 RTN

98*LBL 88

91 ARCL INB X

92 ISG X

93 flBV

94 RTN

95 .ENB.

104

LIST OF REFERENCES

1. Caram, John M- , Development of NATOPS PerformanceSoftware for the H-5SD~~Helicopter, M."S. Thesis, "flavalFosfgracluafe 5c~EooI, HonTierey, California, 1985.

2. Hargrave, Douglas Francis, Develo£raent of the A-

6

/A -6 ETRAM/KA-6D NATOPS Calculator AlHecI PerformancePlanning SysFem (NC][FPsy, ~H.S. Thesis, "NavalPostgraduate School,

-ITonferey , California, 1983.

3. Dixon, H". J., editor, BMDP Statistical Software, .198.1Edition, pp. 264-75, Uni"Berkeley, California, 19 81

4.

Edition, pp.__

_ 264-75, ^ITniversIIy of California Press,, Cc

NATOPS Flight Manual, Navy Model SH-3D/H Helicopters,Navalr 0~T-230~ HTH-T, 0.3. Navy, T93"3~.

5. Hewlett-Packard Company, The HP-41C/CV Alphan umericFull Performance Calculator, ~Owner_[s HandFook" and"Programming £uXcIe, A*prXT "T98Z.

6. Hewlett-Packard Company, HP 82J80A Extended F unction s& Memory Module, Owner^s Manual, July T9~8~4~.

7. Hewlett-Packard Company, HP 82J04A Card Reader, OwnersHandbook, March 1983.

~ "

8. Shevell, Richard S. , Fundamentals of Flight, pp.63-73, Prentice-Hall, IncTT T9S37

9. Hurt, H. H. , Aerodynamics for Naval Aviators, p. 14,The Office of the Chief of TJaval Cperalions, AviationTraining Division, 1965.

105

INITIAL DISTRIBUTION LIST

No. Copies

1. Defence Technical Information Center 2Ca meron S ta ti onAlexandria, Virginia 22314

2. library. Code 142 2Naval Postgraduate SchoolMonterey, California 93943

3. Department Chairman, Code 67 1

Department of AeronauticsNaval Postgraduate SchoolMonterey, California 93943

4- Professor Donald M. Layton, Code 67Ln 5Department of AeronauticsNaval Postgraduate SchoolMonterey, California 93943

5. Cdr William D. Fraser, Code 034 1

Aviation Safety ProgramNaval Postgraduate SchoolMonterey, California 93943

6. Commanding Officer 2Helicopter Antisubmarine Warfare Squadron OneNaval Air StationJacksonville, Florida 32212

7. Commanding Officer 2Helicopter Antisubmarine Warfare Squadron TenNaval Air StationNorth Island, California 92135

8. Commanding Officer 1

Helicopter Antisubmarine Wing OneNaval Air StationJacksonville, Florida 322 12

9. ICDR John T. Curtis. OSN 2Naval Test Pilot SchoolNAS Patuxent River, Maryland 20670

10. IT Mike Caram, CSN 1

USS Tarawa (LHA-1)FPO San Francisco, California 96601

11. Commander, Naval Air Development CenterATTN: Mr. Ralph Carson r Jr. JCode 6051) 1

Warminster, Pennsylvania 189/4

106

1 3 3 7

ThesC95c.lC9582

C9582C « _L

7^

Curtis

Development of NATOPSperformance softwarefor the SH-3D and SH-3Hhelicopters.

H JUL 667 *# 3 1100

ThesisCS582c.l

211198

Curtis

Development of NATOPSperformance softwarefor the SH-3D and SH-3Hhelicopters.

development of natops performance software for the sh-3d

Documents