6. RPM for zero velocity, full throttle setting 7. First power setting 8. Increment of power setting 9. Number of power settings 10. Reverse angle, p if item 6 on card 5 is coded as 2. 3/4 For subsequent cases, repeat all the input data previously specified. For termination, include two blank cards and a third card with 99 coded in an I6 format. Program Output The input prints out initially and then the pertinent data under the following head- ings for options 1 and 2 for forward flight: 1. DUM-FT - propeller diameter, ft. 2. T.S. FPS - tipspeed, fps 3. THRUST or SHP - dependent on which option is selected 4. PNL - perceived noise PNdB, in value corresponds to the number of engines specified in the input. The following cost and weight data prints out when computations are requested. 5. QUANTITY - number of units to be included in cost computation 6. WT-LBS - propeller weight, lbs. 7. $COST - propeller cost in dollars The weight and cost are included for both 1970 and 1980 technology. 8. ANGLE - propeller blade angle in degrees at 3/4 radius which is of particular interest in analyzing fixed pitch propellers. The following data is included as additional information. For example, from an ex- amination of these parameters, an indication of the presence and magnitude of com- pressibility losses and the blade loading characteristics may be established. 9. FT - compressibility correction 21

10. M - free stream Mach number 101.4 VK 11. J - advance ratio = ND SHP (Po/P ) 10" 12. C - power coefficient = 2 N3D5 13. CT - thrust coefficient = 6 1.514 x 10 T( p0/P ) N2D4 For option 3, reverse thrust calculation, the following data prints out. 1. 2. 3. 4. 5. 6. 7. DIA. FT. - propeller diameter, ft. PERCENT THROTTLE - specifies what percent of normal rated power was used. REVERSE ANGLE - reverse angle at 3/4 radius V-KNOTS - landing run velocity REVERSE THRUST - reverse thrust corresponding to 4 above SHP - shaft horsepower corresponding to 4 above RPM - propeller speed corresponding to 4 above The input propeller and operating condition parameters for the parametric studies are varied as follows in the output print outs. For option 1 and 2, forward flight cal- culations, the calculations are made for the input ranges in the following order: 1. Tipspeed 2. Diameter 3. Number of blades 4. Integrated design lift coefficient 5. Activity factor 6. Operating condition 22