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1993-03-05
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PROP SAMPLE RUN: GREAT AMERICA PROP, CONTINENTAL O200, VARIEZE DRAG DATA
CONTROL
NPAYOFF=2
IOPT=1,2,3
END
DESVAR
DIAM=56 PITCH=68 NB=2
RPMREF=2400
TDMAX=.03
END
TABLES
@ CONTINENTAL ENGINE
RPMTAB=800,1300,1700,2000,2200,2400,2600,2800
HPTAB=10,36,56.3,69.5,78.2,87,95.2,103
SFCTAB=.978,.845,.748,.678,.637,.603,.579,.579
END
COMPUTED AF= 98.57
EQUIVALENT CONSTANT CHORD .2R TO TIP= 3.538
THICKNESS RATIO AT 75% STATION = 0.1668
PROP OPTIMIZER (TM) AIRCRAFT CRUISE PROGRAM
Copyright 1992 Donald R Bates/BATES ENGINEERING
2742 Swansboro Road, Placerville, CA 95667
Phone/FAX 916-622-1886
PROP SAMPLE RUN: GREAT AMERICA PROP, CONTINENTAL O200, VARIEZE DRAG DATA
>>>> INITIAL DESIGN:
PROPELLER DESIGN PERFORMANCE
NUMBER OF BLADES = 2 VELOCITY, MPH = 140.988
DIAMETER, INCHES = 56.0000 ALTITUDE, FEET = 8500.00
PITCH, INCHES = 68.0000 DENSITY, SLUGS = 0.183979E-02
BLADE ACTIVITY FACTOR= 98.5670 THRUST, POUNDS = 68.8342
TOTAL ACTIVITY FACTOR= 197.134 DRAG, POUNDS = 68.8341
ADVANCE RATIO, J = 1.10776 THRUST HP = 29.7793
PITCH ANGLE DEG @75%R= 27.2647 HP REQUIRED = 35.2661
BLADE ALPHA DEG @75%R= 2.08418 HP AVAILABLE = 63.9673
THRUST COEF, CT = 0.493047E-01 PROPELLER RPM = 2400.00
POWER COEF, CP = 0.628486E-01 ENGINE RPM = 2400.00
EFFICIENCY, ETA = 0.844418 REDUCT FACTOR = 1.00000
COMPRESS LOSS FACTOR = 1.00000 SFC, LB/HP/HR = 0.603000
EQUIVALENT CNST CHORD= 3.53830 MILES/GALLON = 39.7794
SPEED OF SOUND, FPS = 1083.31 FUEL FLOW, PPH = 21.2655
TIP SPEED, FPS = 621.820 FUEL FLOW, GPH = 3.54425
TIP MACH NUMBER = 0.573998 CAFE SCORE = 3064.13
STA FRACTION SHAPE FACTOR BLADE STATION BLADE CHORD CHORD ANGLE
OF RADIUS ON ECC INCHES INCHES DEGREES
0.2000 1.272 5.600 4.500 62.64
0.3000 1.272 8.400 4.500 52.18
0.4000 1.413 11.20 5.000 44.02
0.5000 1.464 14.00 5.180 37.71
0.6000 1.422 16.80 5.030 32.79
0.7000 1.309 19.60 4.630 28.91
0.8000 1.114 22.40 3.940 25.79
0.9000 0.8394 25.20 2.970 23.24
1.000 0.5087 28.00 1.800 21.13
PROP SAMPLE RUN: GREAT AMERICA PROP, CONTINENTAL O200, VARIEZE DRAG DATA
@ 03/06/93 00:42:12.94
>>>> OPTIMIZED DESIGN:
VARIABLE INITIALLY OPTIMIZED LOWER LIMIT UPPER LIMIT OPTION FLAG
AFTOT 197.134 300.000 140.000 1100.00 IOPT( 1)= 1
DIAM 56.0000 61.3258 40.0000 80.0000 IOPT( 2)= 2
PITCH 68.0000 78.1244 30.0000 120.000 IOPT( 3)= 3
PROPELLER DESIGN PERFORMANCE
NUMBER OF BLADES = 2 VELOCITY, MPH = 174.716
DIAMETER, INCHES = 61.3258 ALTITUDE, FEET = 8500.00
PITCH, INCHES = 78.1244 DENSITY, SLUGS = 0.183979E-02
BLADE ACTIVITY FACTOR= 150.000 THRUST, POUNDS = 105.708
TOTAL ACTIVITY FACTOR= 300.000 DRAG, POUNDS = 105.708
ADVANCE RATIO, J = 1.25355 THRUST HP = 55.6423
PITCH ANGLE DEG @75%R= 28.3987 HP REQUIRED = 63.9673
BLADE ALPHA DEG @75%R= 0.384681 HP AVAILABLE = 63.9673
THRUST COEF, CT = 0.526464E-01 PROPELLER RPM = 2400.00
POWER COEF, CP = 0.745604E-01 ENGINE RPM = 2400.00
EFFICIENCY, ETA = 0.869856 REDUCT FACTOR = 1.00000
COMPRESS LOSS FACTOR = 1.00000 SFC, LB/HP/HR = 0.603000
EQUIVALENT CNST CHORD= 5.89672 MILES/GALLON = 27.1775
SPEED OF SOUND, FPS = 1083.31 FUEL FLOW, PPH = 38.5723
TIP SPEED, FPS = 691.440 FUEL FLOW, GPH = 6.42871
TIP MACH NUMBER = 0.638264 CAFE SCORE = 3311.47
STA FRACTION SHAPE FACTOR BLADE STATION BLADE CHORD CHORD ANGLE
OF RADIUS ON ECC INCHES INCHES DEGREES
0.2000 1.272 6.133 7.499 63.75
0.3000 1.272 9.199 7.499 53.51
0.4000 1.413 12.27 8.333 45.39
0.5000 1.464 15.33 8.633 39.04
0.6000 1.422 18.40 8.383 34.05
0.7000 1.309 21.46 7.716 30.08
0.8000 1.114 24.53 6.566 26.88
0.9000 0.8394 27.60 4.950 24.25
1.000 0.5087 30.66 3.000 22.07
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 6.13
X YU YL
0.0000 0.5427 0.5427
0.1875 1.010 0.2357
0.3750 1.219 0.1492
0.7499 1.482 0.7065E-01
1.500 1.761 0.1564E-01
2.250 1.831 0.0000
3.000 1.808 0.0000
3.750 1.707 0.0000
4.500 1.525 0.0000
5.250 1.257 0.0000
6.000 0.9585 0.0000
6.749 0.6209 0.0000
7.499 0.2944 0.0000
LEADING EDGE RADIUS 0.2392
SQUARED OFF TRAILING EDGE THICKNESS 0.2944
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 9.20
X YU YL
0.0000 0.5427 0.5427
0.1875 1.010 0.2357
0.3750 1.219 0.1492
0.7499 1.482 0.7065E-01
1.500 1.761 0.1564E-01
2.250 1.831 0.0000
3.000 1.808 0.0000
3.750 1.707 0.0000
4.500 1.525 0.0000
5.250 1.257 0.0000
6.000 0.9585 0.0000
6.749 0.6209 0.0000
7.499 0.2944 0.0000
LEADING EDGE RADIUS 0.2392
SQUARED OFF TRAILING EDGE THICKNESS 0.2944
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 12.27
X YU YL
0.0000 0.5427 0.5427
0.2083 1.010 0.2357
0.4166 1.219 0.1492
0.8333 1.482 0.7065E-01
1.667 1.761 0.1564E-01
2.500 1.831 0.0000
3.333 1.808 0.0000
4.166 1.707 0.0000
5.000 1.525 0.0000
5.833 1.257 0.0000
6.666 0.9585 0.0000
7.499 0.6209 0.0000
8.333 0.2944 0.0000
LEADING EDGE RADIUS 0.2392
SQUARED OFF TRAILING EDGE THICKNESS 0.2944
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 15.33
X YU YL
0.0000 0.4999 0.4999
0.2158 0.9303 0.2171
0.4316 1.123 0.1374
0.8633 1.365 0.6507E-01
1.727 1.622 0.1440E-01
2.590 1.686 0.0000
3.453 1.666 0.0000
4.316 1.573 0.0000
5.180 1.405 0.0000
6.043 1.158 0.0000
6.906 0.8829 0.0000
7.769 0.5719 0.0000
8.633 0.2711 0.0000
LEADING EDGE RADIUS 0.2203
SQUARED OFF TRAILING EDGE THICKNESS 0.2711
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 18.40
X YU YL
0.0000 0.4392 0.4392
0.2096 0.8173 0.1907
0.4191 0.9863 0.1207
0.8383 1.199 0.5717E-01
1.677 1.425 0.1265E-01
2.515 1.481 0.0000
3.353 1.463 0.0000
4.191 1.382 0.0000
5.030 1.234 0.0000
5.868 1.018 0.0000
6.706 0.7756 0.0000
7.544 0.5025 0.0000
8.383 0.2382 0.0000
LEADING EDGE RADIUS 0.1935
SQUARED OFF TRAILING EDGE THICKNESS 0.2382
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 21.46
X YU YL
0.0000 0.3758 0.3758
0.1929 0.6994 0.1632
0.3858 0.8440 0.1033
0.7716 1.026 0.4892E-01
1.543 1.219 0.1083E-01
2.315 1.268 0.0000
3.086 1.252 0.0000
3.858 1.182 0.0000
4.630 1.056 0.0000
5.401 0.8707 0.0000
6.173 0.6637 0.0000
6.944 0.4299 0.0000
7.716 0.2038 0.0000
LEADING EDGE RADIUS 0.1656
SQUARED OFF TRAILING EDGE THICKNESS 0.2038
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 24.53
X YU YL
0.0000 0.3266 0.3266
0.1642 0.6078 0.1418
0.3283 0.7334 0.8978E-01
0.6566 0.8917 0.4251E-01
1.313 1.059 0.9410E-02
1.970 1.102 0.0000
2.626 1.088 0.0000
3.283 1.027 0.0000
3.940 0.9177 0.0000
4.596 0.7567 0.0000
5.253 0.5768 0.0000
5.910 0.3736 0.0000
6.566 0.1771 0.0000
LEADING EDGE RADIUS 0.1439
SQUARED OFF TRAILING EDGE THICKNESS 0.1771
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 27.60
X YU YL
0.0000 0.2285 0.2285
0.1237 0.4253 0.9923E-01
0.2475 0.5132 0.6282E-01
0.4950 0.6240 0.2975E-01
0.9899 0.7413 0.6584E-02
1.485 0.7707 0.0000
1.980 0.7614 0.0000
2.475 0.7188 0.0000
2.970 0.6422 0.0000
3.465 0.5294 0.0000
3.960 0.4036 0.0000
4.455 0.2614 0.0000
4.950 0.1239 0.0000
LEADING EDGE RADIUS 0.1007
SQUARED OFF TRAILING EDGE THICKNESS 0.1239
BLADE AIRFOIL COORDINATES
CLARK Y BLADE STATION = 30.66
X YU YL
0.0000 0.1101 0.1101
0.7499E-01 0.2049 0.4780E-01
0.1500 0.2472 0.3026E-01
0.3000 0.3006 0.1433E-01
0.6000 0.3571 0.3172E-02
0.8999 0.3713 0.0000
1.200 0.3668 0.0000
1.500 0.3463 0.0000
1.800 0.3094 0.0000
2.100 0.2551 0.0000
2.400 0.1944 0.0000
2.700 0.1259 0.0000
3.000 0.5971E-01 0.0000
LEADING EDGE RADIUS 0.4851E-01
SQUARED OFF TRAILING EDGE THICKNESS 0.5971E-01
NOTE: Blade chord angle is measured from the plane of rotation.
Blade station is measured from the center of the propeller.
The chord line is along the flat bottom of the airfoil.
Airfoil coordinates are measured along the chord line from
the leading edge (X) and perpendicular to the chord line
(YL = lower surface and YU = upper surface positive up).
Any blade shape that maintains the design chord versus
radial station relationship may be used.
CONSTRAINT VALUES ARE A MEASURE OF THE DEGREE OF OPTIMIZATION.
EQUALITY CONSTRAINTS ARE SATISFIED WHEN = 0
INEQUALITY CONSTRAINTS ARE SATISFIED WHEN => 0
TYPE: EQUALITY = 0, UPPER BOUND = 1, LOWER BOUND = -1
SYSTEM CONSTRAINT VALUES:
NAME TYPE ACTIVE INACTIVE
AFBMAX 1 0.0000
HPREQ 1 0.7108E-06
PAYOFF=-1.749 (-VEL) NRUN= 115 NC= 2 NEC= 0
ELAPSED TIME= 41.520 SEC