Here is Vance's prop program with the line numbers removed and descriptive
labels used for routines.
The input statements are still there so that
is a future changes so one does not have to enter the input data over
and over again.
I also changed the printer output to print to
a file. Better to save paper and better to send over the internet.
I included a sample output file.
BTW if anybody needs the QB 4.5 interpreter / compiler let me know.
Paul Lamar
The Aircraft Rotary Engine Newsletter. Powered by Linux.
http://home.earthlink.net/~rotaryeng/ http://www.linux.org
REM PRPLRITF PROPELLOR PROGRAM FOR ITERATION TO PREDICT ENGINE POWER RQD
REM NO ENGINE POWER CURVES USED JUST REQD POWER PRINTED OUT
REM UPDATED FOR ALTITUDE INPUT
REM PROGRAM FOR STATIC AND MOVING THRUST
DIM BANG(10), WDTH(10)
DIM ANG(30), CL(30), CD(30)
DIM SPD(20), RPM(20)
DIM HPD(80): REM USED IN POWER SUBROUTINES
OPEN "vance.dat" FOR OUTPUT AS #1
REM FIXED DATA
PI = 3.1417
G = 32.18
REM ------------------ INPUT DATA -----------------------
INPUT "INPUT NAME OF CASE ", CASE$
AIRDSL = 2.37689E-03
INPUT "INPUT DESIRED ALTITUDE IN FEET "; ALTF
AIRDEN = 2.37689E-03 * ((1 - 6.8753E-06 * ALTF) ^ 4.2651)
INPUT "INPUT CONDITIONS PROP DIA, PITCH (INCHES) ", DIA, PITCH
INPUT "INPUT BLADE WIDTH AT .9, .7, .5, .3 RADIUS "; WDTH(9), WDTH(7), WDTH(5), WDTH(3)
INPUT "INPUT BLADE ANGLE AT .9, .7, .5, .3 RAD. OR ZEROS FOR TRUE HELICAL PITCH "; BANG(9), BANG(7), BANG(5), BANG(3)
INPUT "INPUT NUMBER OF DESIRED PLANE SPEEDS "; NSPD
FOR NS = 1 TO NSPD
INPUT "INPUT PLANE SPEED MPH "; SPD(NS)
INPUT "INPUT STARTING PROP RPM "; RPM(NS)
NEXT NS
INPUT "INPUT FUSELAGE CROSS SECT AREA SQFT, DRAG COEFF (.2 AVG) "; AFUS, CDFUS
INPUT "INPUT 1 FOR SHORT PRINTOUT 2 FOR LONG "; PCODE
REM --------------------- HARD COPY OF INPUT DATA -------
IF PCODE < .9 THEN GOTO DataForAirFoil: '3200
PRINT #1, "PROGRAM PRPLRITF - FOR THRUST AND POWER AT DESIGNATED SPEEDS AND RPM"
PRINT #1,
PRINT #1, DATE$, TIME$
PRINT #1,
PRINT #1, "CASE "; CASE$; " - ALTITUDE "; ALTF; " FT - DENSITY "; AIRDEN
PRINT #1, " PROP DIA "; DIA; "IN PITCH "; PITCH; "IN"
PRINT #1, " RPM "; RPM
PRINT #1, " BLADE WIDTH @ .9R "; WDTH(9); " .7R "; WDTH(7); " .5R "; WDTH(5);
PRINT #1, " .3R "; WDTH(3)
PRINT #1, " FUSELAGE AREA "; AFUS; " DRAG COEFF "; CDFUS
PRINT #1,
PRINT #1,
DataForAirFoil: ' 3200 REM --- DATA FOR AIR FOIL ---
REM CLARK Y WITH 6 ASPECT RATIO
REM ANG ATT, LIFT COEFF, DRAG COEFF
DATA -35,-1.25,.4
DATA -30,-1.55,.3
DATA -25,-1.4,.15
DATA -20,-1.12, .1
DATA -15, -.74, .04
DATA -10, -.38, .02
DATA -5, 0, .01
DATA 0, .38, .02
DATA 5, .74, .04
DATA 10, 1.12, .1
DATA 15, 1.4, .15
DATA 20, 1.55, .3
DATA 25, 1.25, .4
DATA 30, 1.0, .6
DATA 35, .8, .8
DATA 40, .6, 1
DATA 45, .55, 1.2
DATA 50, .5, 1.5
DATA 55, .45, 1.7
DATA 60, .4, 2
REM LOAD AIRFOIL DATA
FOR N = 1 TO 20
READ ANG(N), CL(N), CD(N)
NEXT N
REM************* SPEED LOOP ***********************
FOR NS = 1 TO NSPD
PVEL = SPD(NS)
PLANEV = PVEL * 88 / 60
IF PCODE = 1 THEN PRINT #1, " MPH RPM THR THR BHP DELTA EFF JET SYS NET(-FUS DRG) ANG ATT"
IF PCODE = 1 THEN PRINT #1, " LBS HP REQ V(FPS) PRP EFF EFF THR THRHP @.9R .7R .3R"
IF PCODE = 1 THEN PRINT #1,
REM***********************************************************
DELRPM = 100
RPM = RPM(NS) - DELRPM
FOR NR = 1 TO 14
RPM = RPM + DELRPM
REM ******************* RPM LOOP **************************
REM ZERO OUT VALUES FOR LOOP
HPTOT = 0
THRTOT = 0
JETTOT = 0
REM COMPUTATIONS
REM LOOP FOR RADIUS POINTS
IF PCODE < 2 THEN GOTO PcodeLessThan2 ' 4150
PRINT #1, "RADIUS "; "WIDTH "; "ANGLE "; "HP ZONE "; "LIFT THRST ";
PRINT #1, "ANG ATT "; "PITCH VEL"
PRINT #1,
PcodeLessThan2: ' 4150 REM
RADT = 0
DELVT = 0
REM ************************************************************
FOR RAD = .3 TO .9 STEP .2
LRAD = INT(.1 + (RAD * 10))
RZMIN = RAD - .1
RZMAX = RAD + .1
WIDZON = WDTH(LRAD)
PLVEL = RPM * DIA * RAD * PI / (12 * 60): REM PITCH LINE VEL - FPS
BLANGT = PITCH / (RAD * DIA * PI)
BLANG = BANG(LRAD) * PI / 180: REM BLADE ANGLE IN RADIANS FROM INPUT LINE
IF BANG(LRAD) < 1 THEN BLANG = ATN(BLANGT): REM BLADE ANGLE IF INPUT ZEROS
BLANGD = BLANG * 180 / PI: REM BLADE ANGLE IN DEGREES
DISCAR = (((RZMAX * DIA) ^ 2) - ((RZMIN * DIA) ^ 2)) * .7854 / 144
BLDAR = DIA * (RZMAX - RZMIN) * WIDZON / 144
REM AREAS IN SQUARE FEET -BLADE AREA FOR TWO BLADES
TOUT = 0
REM
INVFAC = 1!
REM INVFAC IS THE FACTOR FOR INLET VEL RELATIVE TO MOM VEL
REM
REM ---------LOOP FOR DELTA V ----------------------
FOR DELV = 10 TO 190 STEP 10
LoopForDeltaV: ' 4360
AIRVEL = PLANEV + (INVFAC * DELV)
AIRANG = ATN(AIRVEL / PLVEL)
ANGAT = BLANG - AIRANG
ANGATD = ANGAT * 180 / PI
NAFD = INT((ANGATD / 5) + 8)
AIRWF = AIRVEL * AIRDEN * DISCAR
MOMF = AIRWF * DELV
DELCL = CL(NAFD + 1) - CL(NAFD)
DELANG = ANGATD - ANG(NAFD)
CLZON = CL(NAFD) + (DELANG * DELCL / 5)
LFTVEL = PLVEL / COS(AIRANG)
LFTQ = AIRDEN * .5 * (LFTVEL ^ 2)
LIFT = CLZON * LFTQ * BLDAR
DELCD = CD(NAFD + 1) - CD(NAFD)
CDZON = CD(NAFD) + (DELANG * DELCD / 5)
DRAG = CDZON * LFTQ * BLDAR
LIFTHR = LIFT * COS(AIRANG) - DRAG * SIN(AIRANG)
TORDRG = DRAG * COS(AIRANG) + LIFT * SIN(AIRANG)
HPZON = TORDRG * PLVEL / 550
DVHEAD = (DELV ^ 2) / (2 * G)
REM JET HP
EXVEL = PLANEV + DELV
JETHP = LIFTHR * EXVEL / 550
IF MOMF > LIFTHR THEN DELV = DELV - 1: TOUT = 1: GOTO LoopForDeltaV: '4360
IF TOUT > 0 THEN GOTO ExitDeltaVLoop ' 4670
NEXT DELV
REM ---------------- END OF DELT V LOOP ---------------
REM OUT OF LOOP
ExitDeltaVLoop: ' 4670 REM OUT OF LOOP
IF RAD = .9 THEN AAT9 = ANGATD
IF RAD = .7 THEN AAT7 = ANGATD
IF RAD = .5 THEN AAT5 = ANGATD
PRINT USING "#####.##"; RAD; WIDZON; BLANGD; HPZON; LIFTHR;
PRINT USING "#####.##"; ANGATD; PLVEL; DELV
IF PCODE < 1.5 THEN GOTO PcodeLessThan1.5: '4740
PRINT #1, USING "#####.##"; RAD; WIDZON; BLANGD; HPZON; LIFTHR;
PRINT #1, USING "#####.##"; ANGATD; PLVEL
PcodeLessThan1.5: '4740 REM
HPTOT = HPTOT + HPZON
THRTOT = THRTOT + LIFTHR
JETTOT = JETTOT + JETHP
REM DEVICE FOR WEIGHTED AVERAGE OF DELTA V
DELVT = DELVT + RAD * DELV
RADT = RADT + RAD
NEXT RAD
REM ************ CORRECTION FOR ADDED FUSELAGE DRAG *************
DELVA = DELVT / RADT
EXVELA = PLANEV + DELVA
FUSQ = AIRDEN * .5 * (PLANEV ^ 2)
FUSQP = AIRDEN * .5 * (EXVELA ^ 2): REM FUSELAGE Q IN PROPWASH
FUSDRG = FUSQ * AFUS * CDFUS
FUSDRGP = FUSQP * AFUS * CDFUS: REM FUSELAGE DRAG IN PROPWASH
DELDRG = FUSDRGP - FUSDRG
PRINT "FUS DRAG "; FUSDRG; " DRAG IN PROPWASH "; FUSDRGP
REM -------- SUMMATIONS ---------------------------
THRHP = THRTOT * PLANEV / 550
THRNET = THRTOT - DELDRG
EFF = THRHP / HPTOT
JEFF = JETTOT / HPTOT
TVEL = (((PLVEL / .9) ^ 2) + (AIRVEL ^ 2)) ^ .5
NTHRHP = THRNET * PLANEV / 550: REM NET THUST HP
SEFF = NTHRHP / HPTOT: REM SYSTEM PROPULSIVE EFF WITH ADDED FUS DRAG
PRINT "PLANE VEL "; PVEL; " RPM "; RPM; " PITCH "; PITCH
PRINT "TOTAL THRUST "; THRTOT, "TOTAL HP "; HPTOT
PRINT "THRUST HP "; THRHP
PRINT "FUSELAGE ADDED DRAG "; DELDRG; " THRUST MINUS THIS LOSS "; THRNET; " LBS"
IF PCODE = 1 THEN PRINT #1, USING "#####"; PVEL; RPM;
IF PCODE = 1 THEN PRINT #1, USING "#####"; THRTOT; THRHP; HPTOT; DELVT;
IF PCODE = 1 THEN PRINT #1, USING "##.###"; EFF; JEFF; SEFF;
IF PCODE = 1 THEN PRINT #1, USING "######"; THRNET; NTHRHP;
IF PCODE = 1 THEN PRINT #1, USING "####.#"; AAT9; AAT7; AAT5
IF PCODE < 1.5 THEN GOTO PcodeLessThan1.5A '5170
PRINT #1,
PRINT #1, "PLANE SPEED "; PVEL; "MPH RPM "; RPM
PRINT #1, " PITCH AT THIS POINT "; PITCH; " INCHES"
PRINT #1, "APPROX AIR VEL OVER TIP "; TVEL; " FT/SEC"
PRINT #1, "TOTAL THRUST "; THRTOT; " HORSEPOWER REQUIRED "; HPTOT
PRINT #1, "THRUST HP "; THRHP; " PROPELLOR EFF "; EFF
PRINT #1, "FUSELAGE ADDED DRAG "; DELDRG; " THRUST MINUS THIS LOSS "; THRNET; " LBS"
PRINT #1, "JET HORSEPOWER "; JETTOT; " JET HP EFF "; JEFF
PRINT #1, "PROPULSIVE SYSTEM EFF (WITH FUS. DRG) "; SEFF
PRINT #1,
PRINT #1,
PcodeLessThan1.5A: '5170 REM
REM NEW RPM VALUE
NEXT NR
IF PCODE > .1 THEN PRINT #1,
NEXT NS: REM NEXT PLANE SPEED
IF PCODE > .1 THEN PRINT #1,
CLOSE
SHELL "MORE < vance.dat"
SYSTEM
END
PROGRAM PRPLRITF - FOR THRUST AND POWER AT DESIGNATED SPEEDS AND RPM
12-26-1999 00:48:29
CASE paul2 - ALTITUDE 0 FT - DENSITY 2.37689E-03
PROP DIA 72 IN PITCH 50 IN
RPM 0
BLADE WIDTH @ .9R 2 .7R 3 .5R 4 .3R 5
FUSELAGE AREA 8 DRAG COEFF .2
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -13.32 -29.07 -11.38 254.48
0.50 4.00 23.85 -17.69 -38.82 -9.80 424.13
0.70 3.00 17.52 -15.30 -35.25 -8.22 593.78
PLANE SPEED 200 MPH RPM 2700
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 719.2122 FT/SEC
TOTAL THRUST -103.1496 HORSEPOWER REQUIRED -46.30967
THRUST HP -55.0131 PROPELLOR EFF 1.18794
FUSELAGE ADDED DRAG -10.46211 THRUST MINUS THIS LOSS -92.68745 LBS
JET HORSEPOWER -53.10076 JET HP EFF 1.146645
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) 1.067451
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -12.12 -26.34 -10.45 263.90
0.50 4.00 23.85 -15.31 -34.01 -8.94 439.84
0.70 3.00 17.52 -12.25 -29.27 -7.49 615.77
PLANE SPEED 200 MPH RPM 2800
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 742.078 FT/SEC
TOTAL THRUST -89.62291 HORSEPOWER REQUIRED -39.67544
THRUST HP -47.79889 PROPELLOR EFF 1.204747
FUSELAGE ADDED DRAG -9.38092 THRUST MINUS THIS LOSS -80.24199 LBS
JET HORSEPOWER -46.28648 JET HP EFF 1.166628
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) 1.078645
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -10.71 -23.31 -9.55 273.33
0.50 4.00 23.85 -13.16 -29.61 -8.21 455.55
0.70 3.00 17.52 -8.92 -22.78 -6.80 637.77
PLANE SPEED 200 MPH RPM 2900
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 765.0422 FT/SEC
TOTAL THRUST -75.69915 HORSEPOWER REQUIRED -32.7887
THRUST HP -40.37288 PROPELLOR EFF 1.231305
FUSELAGE ADDED DRAG -7.933426 THRUST MINUS THIS LOSS -67.76572 LBS
JET HORSEPOWER -39.26896 JET HP EFF 1.197637
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) 1.102262
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -9.39 -20.53 -8.78 282.75
0.50 4.00 23.85 -10.32 -23.96 -7.43 471.26
0.70 3.00 17.52 -5.32 -15.79 -6.15 659.76
PLANE SPEED 200 MPH RPM 3000
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 788.0963 FT/SEC
TOTAL THRUST -60.27187 HORSEPOWER REQUIRED -25.02871
THRUST HP -32.145 PROPELLOR EFF 1.284325
FUSELAGE ADDED DRAG -6.624878 THRUST MINUS THIS LOSS -53.64699 LBS
JET HORSEPOWER -31.38937 JET HP EFF 1.254135
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) 1.143156
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -7.61 -16.93 -7.94 292.18
0.50 4.00 23.85 -7.72 -18.78 -6.78 486.96
0.70 3.00 17.52 -1.94 -9.27 -5.61 681.75
PLANE SPEED 200 MPH RPM 3100
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 811.5908 FT/SEC
TOTAL THRUST -44.97798 HORSEPOWER REQUIRED -17.27905
THRUST HP -23.98826 PROPELLOR EFF 1.388286
FUSELAGE ADDED DRAG -4.65181 THRUST MINUS THIS LOSS -40.32617 LBS
JET HORSEPOWER -23.53758 JET HP EFF 1.362204
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) 1.244704
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -6.01 -13.67 -7.23 301.60
0.50 4.00 23.85 -4.42 -12.29 -6.07 502.67
0.70 3.00 17.52 2.21 -1.28 -5.03 703.74
PLANE SPEED 200 MPH RPM 3200
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 834.7933 FT/SEC
TOTAL THRUST -27.24472 HORSEPOWER REQUIRED -8.224088
THRUST HP -14.53052 PROPELLOR EFF 1.766824
FUSELAGE ADDED DRAG -3.329544 THRUST MINUS THIS LOSS -23.91518 LBS
JET HORSEPOWER -14.28963 JET HP EFF 1.737534
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) 1.550903
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -3.95 -9.57 -6.45 311.03
0.50 4.00 23.85 -1.36 -6.32 -5.49 518.38
0.70 3.00 17.52 6.61 6.02 -4.55 725.73
PLANE SPEED 200 MPH RPM 3300
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 858.4079 FT/SEC
TOTAL THRUST -9.870762 HORSEPOWER REQUIRED 1.306951
THRUST HP -5.264407 PROPELLOR EFF -4.028008
FUSELAGE ADDED DRAG -1.335953 THRUST MINUS THIS LOSS -8.534809 LBS
JET HORSEPOWER -5.143505 JET HP EFF -3.935501
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) -3.482839
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -2.07 -5.83 -5.79 320.45
0.50 4.00 23.85 2.52 0.95 -4.84 534.09
0.70 3.00 17.52 11.98 14.82 -4.03 747.72
PLANE SPEED 200 MPH RPM 3400
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 881.7363 FT/SEC
TOTAL THRUST 9.943686 HORSEPOWER REQUIRED 12.43405
THRUST HP 5.303299 PROPELLOR EFF .4265143
FUSELAGE ADDED DRAG 0 THRUST MINUS THIS LOSS 9.943686 LBS
JET HORSEPOWER 5.387269 JET HP EFF .4332675
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) .4265143
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 -0.04 -1.87 -5.16 329.88
0.50 4.00 23.85 6.41 7.52 -4.31 549.80
0.70 3.00 17.52 17.12 23.04 -3.60 769.72
PLANE SPEED 200 MPH RPM 3500
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 905.4521 FT/SEC
TOTAL THRUST 28.69271 HORSEPOWER REQUIRED 23.49175
THRUST HP 15.30278 PROPELLOR EFF .6514109
FUSELAGE ADDED DRAG 2.238708 THRUST MINUS THIS LOSS 26.45401 LBS
JET HORSEPOWER 15.4874 JET HP EFF .6592699
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) .6005855
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 2.59 2.84 -4.46 339.30
0.50 4.00 23.85 10.58 14.46 -3.81 565.51
0.70 3.00 17.52 23.21 32.83 -3.12 791.71
PLANE SPEED 200 MPH RPM 3600
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 928.8879 FT/SEC
TOTAL THRUST 50.13834 HORSEPOWER REQUIRED 36.38413
THRUST HP 26.74045 PROPELLOR EFF .734948
FUSELAGE ADDED DRAG 3.739655 THRUST MINUS THIS LOSS 46.39868 LBS
JET HORSEPOWER 27.11784 JET HP EFF .7453205
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) .6801307
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 5.07 7.09 -3.88 348.73
0.50 4.00 23.85 15.04 21.79 -3.32 581.21
0.70 3.00 17.52 29.07 41.98 -2.73 813.70
PLANE SPEED 200 MPH RPM 3700
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 952.6897 FT/SEC
TOTAL THRUST 70.86523 HORSEPOWER REQUIRED 49.1814
THRUST HP 37.79479 PROPELLOR EFF .7684774
FUSELAGE ADDED DRAG 6.003708 THRUST MINUS THIS LOSS 64.86153 LBS
JET HORSEPOWER 38.55299 JET HP EFF .7838938
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) .7033719
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 7.72 11.58 -3.32 358.15
0.50 4.00 23.85 19.79 29.49 -2.86 596.92
0.70 3.00 17.52 35.30 51.58 -2.36 835.69
PLANE SPEED 200 MPH RPM 3800
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 976.5269 FT/SEC
TOTAL THRUST 92.65105 HORSEPOWER REQUIRED 62.80588
THRUST HP 49.41389 PROPELLOR EFF .7867718
FUSELAGE ADDED DRAG 8.283005 THRUST MINUS THIS LOSS 84.36804 LBS
JET HORSEPOWER 50.71749 JET HP EFF .8075278
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) .7164344
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 10.53 16.30 -2.77 367.58
0.50 4.00 23.85 24.83 37.57 -2.42 612.63
0.70 3.00 17.52 42.52 62.86 -1.95 857.68
PLANE SPEED 200 MPH RPM 3900
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 1000.093 FT/SEC
TOTAL THRUST 116.7227 HORSEPOWER REQUIRED 77.88644
THRUST HP 62.25211 PROPELLOR EFF .7992675
FUSELAGE ADDED DRAG 10.04074 THRUST MINUS THIS LOSS 106.682 LBS
JET HORSEPOWER 64.18751 JET HP EFF .8241165
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) .7305128
RADIUS WIDTH ANGLE HP ZONE LIFT THRST ANG ATT PITCH VEL
0.30 5.00 36.38 13.52 21.24 -2.25 377.00
0.50 4.00 23.85 30.18 46.03 -1.99 628.34
0.70 3.00 17.52 49.52 73.39 -1.62 879.68
PLANE SPEED 200 MPH RPM 4000
PITCH AT THIS POINT 50 INCHES
APPROX AIR VEL OVER TIP 1023.999 FT/SEC
TOTAL THRUST 140.6621 HORSEPOWER REQUIRED 93.21758
THRUST HP 75.01981 PROPELLOR EFF .8047818
FUSELAGE ADDED DRAG 12.34689 THRUST MINUS THIS LOSS 128.3152 LBS
JET HORSEPOWER 77.8506 JET HP EFF .8351494
PROPULSIVE SYSTEM EFF (WITH FUS. DRG) .7341405