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COMPUTER PROGRAM USER'S MANUAL FOR ... - CAFE Foundation

COMPUTER PROGRAM USER'S MANUAL FOR ... - CAFE Foundation

HAMILTON STANQARD

HAMILTON STANQARD CflMPUTER DECK Nfl. H43Z COHPUTFS PFoFORYANCE1Y21 SE,dEIGHl,AYD COST FOR GFNFRAL AVIATION PROPELLEKS 1 A17PLANE IN ChTfGPRY 11 SAMPLE CASF 2 Z TH9UST INPUT-TIPSPEEl7 PNll llIAYETE9 VAR. - COST AND WEIGHT IPFRATINT, CONDITION THRUST = @?O. 40. nF EYSINFS = 1. IJNIT FACTDR L.C. = 3.22 4LT-FT 0. .DESIGN FLIGHT Y.=0.762 1000 FACTOR L.C. = 1.02 V-KTAS = TEMP K = 71.2 *1Y. CLhSSIFICATIflN FIELD POINT FT. 2. = 5n0. NIJHREQ OF Rl.AnES= 4. ACTIVITY FACTflR=150. INTFGRATEO DESIGN CL =.500 *** 1970 TECHNPCOGY *** *** 1YAO TECHNOLnGY XXX DIA.FT. T.S.FPS SHP DNL QUANTITY WT-LRS 6C;)ST 'JUAr\lTITY. WT-I.RS $COST ANGLE FT H J 6. 950. 6. 75n. 6. o5C. 5. tc. 550. HV. 9. 750. 8. ,h5'). 9. 550. THRUST = 370. ALT-FT = 7500. V-KTAS = TEMP R = 153.2 407. NLJElYFQ IF 4LADES = 4. DIA.FT. F.S.FPS 6."0 A59. 6.00 750. 6.nO 6qP. 6.00 553. 3.00 350. 9.m 759. 8.o~ h5n. 9.01 55,). 274. 97. i'R10. 1@5. 1033. 5470. 105. 925. 15.2 1.000 0.1077 270. 93. 2810. 100. 78A. 5470. 100. AR4. 18.6 1.030 0.1077 275. 90. 2910. 95. 941. 5470. 95. R43. 23.6 1.030 0.1077 273. 86. 2910. 90. 981. 5470. 90. 794. 30.3 1.000 0.1077 293. 94. 2810. 175. 1729. 5470. 175. 1548. 11.5 1.000 0.1077 250. 89. 2810. 165. 1631. 5470. 165. 14.0 1.000 1460. 0.1077 243. 85. 2910. 156. 1539. 5470. 156. 1378. 17.5 1.000 0.1077 242. 91. 2910. 147. 1451. 5470. 147. 1299. 22.5 1.noo 0.1077 3DFRATINC CONDITION N'I. ClF FhlGtNFS = 1. nEsIrx FLIGHT ~.=0.762 CLASSIFICATION = FIELD POINT FT = 2. 0. StIP 226. 213. 70P. 217. 262. ?32. 715. 70 7. PNL 0. n. 0. 0. n. n. 0. 0. ACT IV ITY FACTflQ- 150, ANGLE FT H J 23.5 1.OO'l !).7534 1.019 76.4 1.010 P.7534 1.155 31.5 1.000 0.7534 1.333 77.9 1 . n ~ 0.2534 1.575 23.0 1.oon 0.2534 1.019 25.1 1.0nn 9.2534 I .155 29.1 34.3 1.090 I .m)n 0.7534 1.333 ~7.2~34 1.575 CP 0.3919 0.1259 0.1991 0.3179 0. C59R 0.0773 0.1099 0. 1747 CT q.0739 0 .O950 0. I264 0.1766 0.041 h o .n534 0.0711 0.0993 FIGURE 12. SAMPLE OUTPUT - THRUST OPTION Ik!TE3RATED DFSIGN CL =.500 " .. . . .. . . ~... . . " 0.445 0.504 0.582 0.687 0.445 0.504 0.582 0.6R7 CP 0.0888 0.1276 0.1993 0.3268 0.0535 0. 0690" 0.0992 0.1634 CT . " 0.1309 0.1682 0.2239 -0.3127 0.0737 0.0946. 0.1260 0.1759 "

HAMILTON SlANDARD COMPUTER DECK NO. H432 COMPUTES PERFORHANCEINOISE~WEIGHT~ANO COST FOR GENERAL AVIATION PROPELLERS 1 AIRPLANE IN CATEGORY 1V SAMPLE CASE 3 2 SHP INPUT-CALC. TIPSPEED FOR 50PERCENT STALL-COST FOR RANGE QUANT. OPERATING CONOITION SHP ALT-FT = = 740. 0. NO. OF ENGINES = 2. DESIGN FLIGHT M.=0.327 UNIT FACTOR L.C. 1000 FACTOR L.C. = 3.22 = 1.02 V-KTAS = 77.5 CLISSIFICATION = 4. TEMP R = 519. FIELO POINT FT. = 500. NUMBER BLAOES= OF 4. ACTIVITY FACTOR-200. INTEGRATED DES1G.N CL =.600 *** 1970 TFCHNOLOGY *** *** 1980 TECHNOLOGY *** 0IA.FT. T.S.FPS THRUST PNL QUANTITY WT-LBS SCOST QUANTITY UT-LBS SCOST ANGLE FT M J CP CT. - a. 345. BLR. 77. 1. 228. 7106. 1. 185. 7770. 46.3 1.000 0.1172 1.194 0.9333 0.4473 1001. 228. 2252. 1001. 1a5. 2463. 2001. 228. 2~07. 2001. 185. 2195. 3001. 22a. 1876. 3001. 185. 2052. 4001. 228. 1788. 4001. 185. 1956. NUMBFR OF BLADES= 6. ACTIVITY FACTOR=200. INTEGRATED DESIGN CL =.600 *** 1970 TECHNOLOGY *a* *** 1980 TECHNOLOGY *** DIA.FT. T.S.FPS THRUST PNL QUANTITY WT-LBS SCOST QUANTITY UT-LBS SCOST ANGLE FT M J CP CT 8. 282. 828. 74. 1. 306. 11926. 1. 245. 12887. 1001. 306. 3780. 1001. 245. 4084. 2001. 306. 3368. 2001. 245. 3640. 3001. 306. 3149. 3001. 245. 3403. 4001. 306. 3002. 4001. 245. 3244. FIGURE 13. SAMPLE OPTION - 50% STALL OPTION 51.2 1.000 0.1171 1.459 1.7021 0.6759

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