 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
