                          RV-6A CAFE FLIGHT TEST                                 
 CONTROL
  NPAYOFF=2          @ Maximum cruise
  IOPT=1,2,3
 END
 DESLIM
  AFLIM=70,120
  DLIM=50  74
 END
 DESVAR
  DIAM=70   PITCH=74
  DREF=70
  RPMREF=2618     ALTCRS=7079
  WTGRSS=1634    SPAN=23
  KS=1.7
  OSWALD=.851
  VDES=199.7
  ADRAG=  2.27865610328028
  BACAL=  4.28878715137178
 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
  RPMTAB=2250   2700
  HPTAB=164  180
  SFCTAB=.67 .54
 END
 EOF

 COMPUTED AF=  85.30    
 THICKNESS RATIO AT 75% TIP STATION =  0.1394    

                         RV-6A CAFE FLIGHT TEST                                 
 @ 11/03/93  10:17:20.04

 >>>> OPTIMIZED DESIGN:

 VARIABLE   INITIALLY    OPTIMIZED    LOWER LIMIT  UPPER LIMIT       OPTION FLAG

 AFDES      85.2985      83.1075      70.0000      120.000           IOPT( 1)= 1
 DIAM       70.0000      72.1851      50.0000      74.0000           IOPT( 2)= 2
 RPM        2618.00      2700.00      2250.00      2700.00           IOPT( 3)= 3

 PROPELLER DESIGN                           CRUISE PERFORMANCE

 NUMBER OF BLADES     =   2                 VELOCITY, MPH  =  201.255    
 BLADE ACTIVITY FACTOR=  83.1075            ALTITUDE, FEET =  7079.00
 DIAMETER, INCHES     =  72.1851            DENSITY, SLUGS = 0.192319E-02
 EFFECTIVE PITCH, IN  =  84.6035            THRUST, POUNDS =  225.513    
 PITCH ANGLE DEG @75%R=  26.4470            DRAG, POUNDS   =  225.513    
 BLADE ALPHA DEG @75%R=  1.61257            THRUST HP      =  121.028    
 DESIGN LIFT COEF, CL =   0.2475            SHAFT HP       =  139.577    
 THRUST COEF, CT      =   0.0442            HP AVAILABLE   =  139.577    
 POWER COEF, CP       =   0.0556            PROPELLER RPM  =  2700.00    
 SPEED_POWER COEF, CS =   1.9434            ENGINE RPM     =  2700.00    
 ADVANCE RATIO, J     =  1.09043            REDUCT FACTOR  =  1.00000    
 EFFICIENCY, ETA      = 0.867105            SFC, LB/HP/HR  = 0.540000    
 ETA COMPRESS CORRECT.=    0.00%            MILES/GALLON   =  16.0210    
 ETA PROFILE DRAG CORR=   -0.03%            FUEL FLOW, PPH =  75.3718    
 ETA DIAMETER CORRECT.=    0.36%            FUEL FLOW, GPH =  12.5620    
 ADRAG, SQ FT         =  2.27866            SOUND SPEED,FPS=  1088.92    
 PITCH CALIBRTN, BACAL=  4.28879            TIP SPEED, FPS =  900.181    
 RATED PITCH, INCHES  =  69.2646            TIP MACH NUMBER= 0.826677    


 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

  ETAMAX     0     0.1233E-06

 PAYOFF=-2.01455      (-VDES)                          NRUN=  43  NC= 1  NEC= 1


                        PROGRAM OUTPUT DEFINITIONS

                                                                          
     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 zero-lift-line pitch angle at 75% tip radius station   
     (pitch) 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.


                        PROGRAM OUTPUT DEFINITIONS

     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.                               


                        PROGRAM OUTPUT DEFINITIONS

     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                                 
                                                                          
     HP      Maximum Horsepower Available (HPA) from the engine at        
             a given RPM.                                                 


                        PROGRAM OUTPUT DEFINITIONS

     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                          
                                                                          
     SHAFT HP: Required input horsepower to the propeller shaft (SHP)     
             before efficiency losses.                                    
                                                                          
     THRUST  Propeller thrust, pounds                                     


                        PROGRAM OUTPUT DEFINITIONS

     THRUST HP: Net horsepower (THP) 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.      

                    ELAPSED RUN TIME=  24.550 SEC

                      PROP OPTIMIZER (tm) v1.90
          Copyright 1993 Donald R Bates - All Rights Reserved
    BATES ENGINEERING, 2742 Swansboro Road, Placerville, CA 95667
                       Phone/FAX 916-622-1886


                         Copy Date 10/31/93
