XFOIL Version 6.96 Calculated polar for: KC-135 BL52.44 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.500 -0.5629 0.08677 0.08428 -0.0468 1.0000 0.0314 -12.250 -0.6033 0.07650 0.07391 -0.0539 1.0000 0.0314 -12.000 -0.6355 0.06967 0.06695 -0.0577 1.0000 0.0314 -11.750 -0.6592 0.06488 0.06206 -0.0594 1.0000 0.0315 -11.500 -0.6826 0.06079 0.05785 -0.0598 1.0000 0.0316 -11.250 -0.7037 0.05749 0.05442 -0.0588 1.0000 0.0316 -11.000 -0.8387 0.04513 0.04099 -0.0445 1.0000 0.0259 -10.750 -0.8305 0.04340 0.03928 -0.0428 1.0000 0.0262 -10.500 -0.8238 0.04218 0.03806 -0.0405 1.0000 0.0264 -10.250 -0.8351 0.03736 0.03293 -0.0360 1.0000 0.0236 -10.000 -0.8508 0.03265 0.02774 -0.0302 1.0000 0.0230 -9.750 -0.8361 0.03054 0.02542 -0.0291 0.9979 0.0232 -9.500 -0.8082 0.02745 0.02199 -0.0305 0.9912 0.0233 -9.250 -0.7764 0.02507 0.01935 -0.0322 0.9845 0.0234 -9.000 -0.7437 0.02329 0.01740 -0.0338 0.9751 0.0237 -8.750 -0.7065 0.02177 0.01573 -0.0363 0.9658 0.0242 -8.500 -0.6658 0.02037 0.01419 -0.0394 0.9544 0.0247 -8.250 -0.6224 0.01924 0.01289 -0.0429 0.9374 0.0255 -8.000 -0.5823 0.01779 0.01137 -0.0461 0.9129 0.0263 -7.750 -0.5546 0.01721 0.01071 -0.0464 0.8801 0.0272 -7.500 -0.5341 0.01672 0.01008 -0.0451 0.8519 0.0279 -7.250 -0.5150 0.01627 0.00949 -0.0436 0.8298 0.0289 -7.000 -0.4959 0.01584 0.00893 -0.0420 0.8125 0.0298 -6.750 -0.4799 0.01516 0.00816 -0.0399 0.7981 0.0309 -6.500 -0.4616 0.01472 0.00767 -0.0383 0.7860 0.0320 -6.250 -0.4412 0.01440 0.00728 -0.0370 0.7749 0.0337 -6.000 -0.4193 0.01414 0.00693 -0.0358 0.7653 0.0354 -5.750 -0.4026 0.01356 0.00631 -0.0339 0.7562 0.0376 -5.500 -0.3805 0.01328 0.00600 -0.0329 0.7483 0.0397 -5.250 -0.3582 0.01301 0.00565 -0.0319 0.7406 0.0421 -5.000 -0.3374 0.01263 0.00526 -0.0307 0.7337 0.0453 -4.750 -0.3137 0.01241 0.00500 -0.0299 0.7265 0.0483 -4.500 -0.2922 0.01206 0.00460 -0.0288 0.7201 0.0522 -4.250 -0.2681 0.01183 0.00435 -0.0281 0.7134 0.0566 -4.000 -0.2454 0.01150 0.00402 -0.0271 0.7068 0.0631 -3.750 -0.2221 0.01124 0.00373 -0.0262 0.7008 0.0735 -3.250 -0.2031 0.00863 0.00275 -0.0204 0.6891 0.4730 -3.000 -0.1794 0.00855 0.00275 -0.0195 0.6837 0.5243 -2.750 -0.1539 0.00851 0.00277 -0.0189 0.6780 0.5479 -2.500 -0.1274 0.00852 0.00275 -0.0185 0.6724 0.5637 -2.250 -0.1006 0.00859 0.00274 -0.0181 0.6671 0.5767 -2.000 -0.0741 0.00861 0.00276 -0.0178 0.6615 0.5898 -1.750 -0.0474 0.00860 0.00277 -0.0174 0.6561 0.6004 -1.500 -0.0202 0.00867 0.00275 -0.0172 0.6512 0.6095 -1.250 0.0069 0.00865 0.00276 -0.0170 0.6462 0.6185 -1.000 0.0338 0.00868 0.00276 -0.0167 0.6408 0.6279 -0.750 0.0611 0.00864 0.00274 -0.0165 0.6357 0.6349 -0.500 0.0889 0.00868 0.00272 -0.0165 0.6307 0.6401 -0.250 0.1166 0.00866 0.00269 -0.0164 0.6252 0.6449 0.000 0.1443 0.00861 0.00265 -0.0163 0.6200 0.6497 0.250 0.1721 0.00864 0.00264 -0.0163 0.6154 0.6549 0.500 0.1997 0.00863 0.00265 -0.0163 0.6104 0.6601 0.750 0.2274 0.00860 0.00263 -0.0162 0.6051 0.6652 1.000 0.2547 0.00860 0.00261 -0.0161 0.5990 0.6709 1.250 0.2816 0.00857 0.00260 -0.0158 0.5912 0.6771 1.500 0.3086 0.00855 0.00257 -0.0156 0.5843 0.6831 1.750 0.3357 0.00855 0.00259 -0.0155 0.5787 0.6896 2.000 0.3629 0.00855 0.00262 -0.0153 0.5726 0.6968 2.250 0.3898 0.00855 0.00264 -0.0151 0.5671 0.7042 2.500 0.4167 0.00857 0.00269 -0.0150 0.5616 0.7130 2.750 0.4434 0.00854 0.00273 -0.0147 0.5554 0.7219 3.000 0.4700 0.00858 0.00277 -0.0144 0.5496 0.7324 3.250 0.4961 0.00856 0.00284 -0.0141 0.5435 0.7443 3.500 0.5220 0.00854 0.00290 -0.0137 0.5366 0.7582 3.750 0.5475 0.00855 0.00297 -0.0132 0.5301 0.7751 4.000 0.5727 0.00851 0.00306 -0.0126 0.5223 0.7955 4.250 0.5973 0.00852 0.00314 -0.0119 0.5147 0.8212 4.500 0.6226 0.00847 0.00326 -0.0113 0.5058 0.8518 4.750 0.6497 0.00850 0.00338 -0.0110 0.4966 0.8851 5.000 0.6822 0.00856 0.00354 -0.0120 0.4850 0.9146 5.250 0.7202 0.00869 0.00371 -0.0142 0.4711 0.9359 5.500 0.7592 0.00886 0.00389 -0.0166 0.4549 0.9508 5.750 0.7962 0.00909 0.00407 -0.0188 0.4336 0.9622 6.000 0.8305 0.00936 0.00427 -0.0203 0.4051 0.9725 6.250 0.8659 0.00981 0.00457 -0.0224 0.3675 0.9792 6.500 0.8990 0.01038 0.00495 -0.0241 0.3276 0.9865 6.750 0.9325 0.01104 0.00541 -0.0260 0.2872 0.9931 7.000 0.9681 0.01170 0.00587 -0.0285 0.2498 0.9985 7.500 1.0012 0.01255 0.00655 -0.0251 0.2142 1.0000 7.750 1.0145 0.01289 0.00685 -0.0226 0.2024 1.0000 8.000 1.0275 0.01325 0.00718 -0.0200 0.1917 1.0000 8.250 1.0394 0.01365 0.00753 -0.0173 0.1811 1.0000 8.500 1.0535 0.01398 0.00786 -0.0150 0.1713 1.0000 8.750 1.0658 0.01437 0.00822 -0.0124 0.1616 1.0000 9.250 1.0867 0.01519 0.00899 -0.0065 0.1432 1.0000 9.500 1.0934 0.01562 0.00941 -0.0030 0.1352 1.0000 9.750 1.1016 0.01609 0.00986 0.0002 0.1267 1.0000 10.000 1.1111 0.01661 0.01038 0.0029 0.1184 1.0000 10.250 1.1192 0.01725 0.01099 0.0056 0.1099 1.0000 10.500 1.1280 0.01794 0.01166 0.0080 0.1003 1.0000 10.750 1.1368 0.01872 0.01242 0.0102 0.0908 1.0000 11.000 1.1436 0.01967 0.01334 0.0124 0.0798 1.0000 11.250 1.1485 0.02084 0.01444 0.0146 0.0682 1.0000 11.500 1.1526 0.02218 0.01573 0.0165 0.0583 1.0000 11.750 1.1574 0.02358 0.01711 0.0182 0.0512 1.0000 12.000 1.1622 0.02507 0.01861 0.0196 0.0458 1.0000 12.250 1.1663 0.02671 0.02025 0.0209 0.0422 1.0000 12.500 1.1738 0.02815 0.02174 0.0218 0.0398 1.0000 12.750 1.1771 0.02996 0.02358 0.0228 0.0377 1.0000 13.000 1.1803 0.03186 0.02553 0.0236 0.0364 1.0000 13.250 1.1869 0.03351 0.02727 0.0243 0.0350 1.0000 13.500 1.1920 0.03532 0.02913 0.0248 0.0337 1.0000 13.750 1.1942 0.03744 0.03130 0.0253 0.0327 1.0000 14.000 1.1903 0.04014 0.03404 0.0259 0.0315 1.0000 14.250 1.1940 0.04222 0.03620 0.0262 0.0309 1.0000 14.500 1.1971 0.04442 0.03849 0.0264 0.0303 1.0000 14.750 1.2014 0.04655 0.04070 0.0264 0.0292 1.0000 15.000 1.2029 0.04902 0.04324 0.0264 0.0285 1.0000 15.250 1.2023 0.05180 0.04608 0.0263 0.0278 1.0000 15.500 1.1990 0.05490 0.04921 0.0260 0.0271 1.0000 15.750 1.1942 0.05818 0.05256 0.0258 0.0265 1.0000 16.000 1.1963 0.06087 0.05535 0.0254 0.0261 1.0000 16.250 1.1977 0.06371 0.05829 0.0248 0.0255 1.0000 16.500 1.1974 0.06672 0.06139 0.0243 0.0251 1.0000 16.750 1.1978 0.06978 0.06453 0.0235 0.0244 1.0000 17.000 1.1967 0.07306 0.06787 0.0226 0.0238 1.0000 17.250 1.1940 0.07656 0.07143 0.0217 0.0233 1.0000 17.500 1.1890 0.08026 0.07516 0.0208 0.0228 1.0000 17.750 1.1852 0.08377 0.07873 0.0201 0.0224 1.0000 18.000 1.1835 0.08733 0.08241 0.0189 0.0221 1.0000 18.250 1.1810 0.09116 0.08635 0.0174 0.0217 1.0000 18.500 1.1781 0.09486 0.09014 0.0163 0.0215 1.0000 18.750 1.1741 0.09897 0.09436 0.0146 0.0210 1.0000 19.000 1.1711 0.10285 0.09832 0.0131 0.0206 1.0000