1、k .” c -a “ - 1. ”- NASA CONTRACT0.R REPORT *o *o 0 cv = U I COMPUTER PROGRAM USERS MANUAL FOR ADVANCED GENERAL AVIATION PROPELLER STUDY by Rose Worobel Prepared by HAMILTON STANDARD , Windsor Locks, Conn. for Advanced Concepts and Missions Division Ofice of Advanced Research and Technology ?I :! Mo
2、flett Field, Cui$ 94035 ? d I IONAL AERONAUTICS AND SPACE ADMlN “I LOAN COPY: RETURN TO AFWL (DOUL) KIRTLAND AFB. N. M. ISTRATION WASHINGTON, D. C. MAY 1972 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1. Report No. 2. Government Accession No. NAS
3、A CR-2066 I 4. Title and Subtitle “Computer Program Users Manual for Advanced General Aviation Propeller Slxdy“ 7. Author(s) Rose Worobel 9. Performing Organization Name and Address Hamilton Standard Division of United Aircraft Corporation Windsor Locks, Connecticut 12. Sponsoring Agency Name and Ad
4、dress National Aeronautics code = 0. when no noise calculation is to be made. 9 fPS 10. Code = 1. for computing the tipspeed corresponding to 50% stall. The option should be used for take-off conditions only. 11. Code = 1. if cost and weight are to be computed. This option must be used with a take-o
5、ff condition. For option 3, reverse thrust calculation, code 4. Landing touch down speed, knots true airspeed 5. Temperature, OF 20 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6. RPM for zero velocity, full throttle setting 7. First power setting
6、 8. Increment of power setting 9. Number of power settings 10. Reverse angle, p if item 6 on card 5 is coded as 2. For subsequent cases, repeat all the input data previously specified. For ter- 3/4 mination, include two blank cards and a third card with 99 coded in an I6 format. Program Output The i
7、nput 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 in PNdB, value corresponds to
8、 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
9、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 presenc
10、e and magnitude of com- pressibility losses and the blade loading characteristics may be established. 9. FT - compressibility correction 21 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10. M - free stream Mach number 101.4 VK ND 11. J - advance ra
11、tio = SHP (Po/P ) 10“ 12. C - power coefficient = 2 N3D5 1.514 x 10 T( p0/P ) 6 13. CT - thrust coefficient = 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 rate
12、d 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
13、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.
14、 Operating condition 22 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-For the option where tipspeed for 50% stall is to be defined, the computations are made for theinput ranges as follows: 1. Diameter 2. Number of blades 3. Activity factor 4. Inte
15、grated design lift coefficient 5. Operating condition For option 3, reverse thrust calculation, the calculations are made for the input ranges in the following order. 1. Throttle setting 2. Diameter 3. Number of blades 4. Activity factor 5. Integrated design lift coefficient 6. Operating condition M
16、ESSAGES A series of messages print out which indicate that the limits of the generaliza- tions have been exceeded. These are listed below. 1. INPUT ERROR IW = 12, IC = 12 - the input item specifying which option is to be used has been included as other than l., 2. or 3., the only option values . 2.
17、ILLEGAL ACTIVITY FACTOR = F8.1 - the input AF exceeds the per- missible 80-200 AF range. 3. ILLEGAL NUMBER OF BLADES = F8.1 - the input number of blades ex- ceeds the permissible 2-8 blades. 4. ILLEGAL INTEGRATED DES. CL = F8.1 - the input CL exceeds the permissible range of 0.3 to 0.8 CL. 23 Provid
18、ed by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-5. 6. 7. 8. ADVANCE RATIO TOO HIGH - check to see that input diameter, RPM, and velocity are correct. The advance ratio limits are 0 to 5. FAILED STALL ITERATION - problem encountered in defining tipspeed cor
19、responding to 50% stall. If this message is encountered, check input for SHP, RPM, altitude, velocity, and diameter. * - print out under PNL indicates that the propeller is operating at a condition where it is more than 50% stalled. * - printout under SHP or THRUST indicates that this condition is o
20、ff the limits of the performance curves. Sample Cases Input coding sample cases for the four performance computation options are shown on figure 10 and the output presented as figures 11 through 14 respectively. The sample cases are presented in the following order. 1. The condition is defined by SH
21、P and tipspeed variation. Performance and cost calculations based on the information included in the computer program is requested. 2. The condition is defined by a thrust requirement and tipspeed variation. Only performance calculations are requested. 3. The condition is defined by SHP. Tipspeed co
22、rresponding to 50% stall and cost for a span of quantities will be computed. 4. Reverse thrusts are required for a given propeller geometry for a range of throttle settings. Computer Running Time The computer program has been run on an IBM-System/37O. Approximately 1000 operating conditions are comp
23、uted per minute. 24 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CONCLUDING REMARKS 1. Generalizations of analytical methods for accurately predicting propeller performance, noise, weight and cost for general aviation aircraft applica- tion have b
24、een made. 3. The computer program offers many options for performing parametric propeller studies for general aviation aircraft. 4. Computer program listings and detailed input and output instructions are presented. 25 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
