                          RV-6A CAFE FLIGHT TEST                                 
 CONTROL
  IOPT=1,2,3,4,5
 END
 DESLIM
  AFLIM=60,150
  DMAX= 72
 END
 DESVAR
  DIAM=70   PITCH=74
  RPMCRS=2618     ALTCRS=7079
  WTGRSS=1634    SPAN=23
  KS=1.85
  OSWALD=.851
  VCRS=190
  ADRAG=2.32
 END
 TABLES
  STA=.2,.3,.4,.5,.6,.7,.8,.9,1.
  CHORD=5.217  5.138  5.090  5.023  4.852  4.527  4.080  3.424  2.651
  TCTAB=.4064  .2937  .2436  .2007  .1684  .1440  .1355  .1151  .0902
 @@@ Typical engine input not available on demo @@@
 @  RPMTAB=1800  2250   2700
 @  HPTAB=132  164  180
 @  SFCTAB=.6  .55  .52
 END
 EOF
                         RV-6A CAFE FLIGHT TEST                                 
 @ 04/04/95  17:28:59.67

 >>>> OPTIMIZED DESIGN:

      VARIABLE   INITIALLY    OPTIMIZED        LOWER LIMIT  UPPER LIMIT

       AFDES      81.3217      85.5585          60.0000      150.000    
       DIAM       70.0000      72.0000          14.4000      72.0000    
       PITCH      74.0000      65.2325          37.0000      148.000    
       RPM        2618.00      2700.00          1800.00      2700.00    
       VCRS       190.000      199.454          142.500      237.500    

 PROPELLER DESIGN                           CRUISE PERFORMANCE

 NUMBER OF BLADES     =   2                 VELOCITY, MPH  =  199.454    
 BLADE ACTIVITY FACTOR=  85.5585            ALTITUDE, FEET =  7079.00
 DIAMETER, INCHES     =  72.0000            DENSITY, SLUGS = 0.192319E-02
 GEOMETRIC PITCH, IN  =  65.2325            THRUST, POUNDS =  227.407    
 EFFECTIVE PITCH, IN  =  78.0085            DRAG, POUNDS   =  227.407    
 ABSOLUTE PITCH, IN   =  83.7306            THRUST HP      =  120.952    
                                            SHAFT HP       =  139.577    
 ALPHA @ 0LL DEG @75%R=  1.57471            HP AVAILABLE   =  139.577    
 DESIGN LIFT COEF, CL =   0.2433            PROPELLER RPM  =  2700.00    
 THRUST COEF, CT      =   0.0451            ENGINE RPM     =  2700.00    
 POWER COEF, CP       =   0.0563            REDUCT FACTOR  =  1.00000    
 ADVANCE RATIO, J     =  1.08345            SFC, LB/HP/HR  = 0.520000    
                                            MILES/GALLON   =  16.4882    
 EFFICIENCY, ETA      = 0.866561            FUEL FLOW, PPH =  72.5803    
 ETA COMPRESS CORRECT.=    0.00%            FUEL FLOW, GPH =  12.0967    
 ETA PROFILE DRAG CORR=   -0.06%            SOUND SPEED,FPS=  1088.92    
 ETA DIAMETER CORRECT.=    0.33%            TIP SPEED, FPS =  897.256    
 ADRAG, SQ FT         =  2.32000            TIP MACH NUMBER= 0.823991    


 CONSTRAINT VALUES MEASURE THE SUCCESS OF THE        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      REQUIREMENT

      CRUISE SHP=HPA     0    -0.1534E-08                  SATISFIED
         THRUST=DRAG     0    -0.1579E-08                  SATISFIED
        ALPHA>=ABMIN    -1                     1575.       SATISFIED

 PAYOFF=-96.4353      (-VCRS)                          TRIAL RUNS = 103


                           GENERAL NOMENCLATURE

     AFDES   Activity factor per blade. The higher the activity factor,   
             the more power a blade can absorb (or is required). For a    
             given diameter, activity factor increases with blade width.  
                                                                          
     ALPHA   Blade angle-of-attack at the 75% radius, degrees. The angle  
             the incoming air flow makes with the airfoil zero-lift-line. 
                                                                          
     ANGLE   Blade pitch angle at 75% tip radius station measured
             with respect to the plane of rotation, degrees.     
                                                                          
     CL      Blade lift coefficient. Design lift coefficient for cruise.  
                                                                          
     CP      Power coefficient: A non dimensional ratio relating power     
             required to air density, propeller speed squared and         
             propeller diameter raised to the fifth power. Power          
             required is proportional to the fifth power of diameter
             for other factors being equal.


                           GENERAL NOMENCLATURE

     CT      Thrust coefficient: A non dimensional ratio relating thrust   
             produced to air density, propeller speed squared and         
             propeller diameter raised to the fourth power. Thrust        
             produced is proportional to the fourth power of diameter     
             for other factors being equal.                               
                                                                          
     CS      SPEED_POWER coefficient, J/CP^(1/5). A design parameter used 
             in determining maximum efficiency for cruise propellers.     
                                                                          
     DIAM    Propeller diameter, inches                                   
                                                                          
     DRAG    Aircraft drag, pounds                                        
                                                                          
     ETA     Propeller efficiency: ETA=CT*J/CP                            
             A measure of how much power is delivered to the air stream   
             by the propeller relative to power delivered by the engine.  
             This value includes compressibility, profile drag and        
             relative diameter corrections.                               


                           GENERAL NOMENCLATURE

     ETA COMPRESS CORRECT: A factor indicating the percentage propeller   
             efficiency is reduced due to sonic compressibility effects   
             at the blade tip. Zero indicates no compressibility losses.  
             The optimizer tries to design on balance to minimum loss.    
                                                                          
     ETA PROFILE DRAG CORR: An efficiency correction due to blade width   
             or total activity factor and represents the induced losses.  
                                                                          
     ETA DIAMETER CORRECT: Corrects for the relative influence of body    
             and engine nacelle size to propeller diameter. Assuming that 
             the reference point is accounted for in the effective pitch  
             and ADRAG calibration, this correction is the increase or    
             decrease in efficiency from the calibrated reference point.  
                                                                          
     FFGPH   Fuel flow in gallons per hour                                
                                                                          
     FFPPH   Fuel flow in pounds per hour                                 
                                                                          
     HPA     Maximum Horsepower Available from the engine at any          
             given engine rpm.                                            


                           GENERAL NOMENCLATURE

     J       Advance ratio J=(V*88)/(RPM*DIAMETER)  Where: V=mph,         
             DIAMETER=ft. In flight the propeller advances a distance     
             of J times the DIAMETER per revolution.                      
                                                                          
     MPG     Aircraft miles per gallon of fuel                            
                                                                          
     NB      Number of blades                                             
                                                                          
     PITCH   Pitch of chord line at the 75% radius station, inches.       
             The geometric or theoretical advance of the propeller        
             per revolution.                                              
                                                                          
     RHO     Atmospheric density, slugs                                   
                                                                          
     SFC     Specific fuel consumption, lb/hp/hr                          
                                                                          
     SHP     Shaft horsepower required at the propeller shaft before      
             efficiency losses.                                           
                                                                          
     THRUST  Propeller thrust, pounds                                     


                           GENERAL NOMENCLATURE

     THP     Net Thrust Horsepower delivered to the atmosphere by the     
             propeller after efficiency losses and required for flight,   
             (THP=SHP*ETA).                                               
                                                                          
     TPMACH  Tip Mach number                                              
                                                                          
     V       Aircraft velocity, miles/hour                                
                                                                          
     VS      Speed of sound, feet/second                                  
                                                                          
     VT      Tip speed, feet/second                                       
                                                                          
     NRUN    Number of trial designs run                                  
                                                                          
     PAYOFF  Objective or merit function. A quantitative measure of       
             the design goal such as maximum velocity or climb rate.      


                         PROP OPTIMIZER (tm)
          Copyright 1994 Donald R Bates - All Rights Reserved
    BATES ENGINEERING, 2742 Swansboro Road, Placerville, CA 95667
                       Phone/FAX 916-622-1886


                         Copy Date 12/11/94
