The Game Master (3rd Edition)

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Text File | 1993-09-09 | 13.5 KB | 338 lines

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 @ 09/09/93 16:36:46.06 >>>> 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= 31.470 SEC