XFOIL Version 6.96 Calculated polar for: PROPFAN CRUISE MISSILE WING AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5598 0.09028 0.08540 -0.0167 1.0000 0.0294 -8.500 -0.5601 0.08565 0.08082 -0.0192 1.0000 0.0282 -8.250 -0.5625 0.08047 0.07569 -0.0234 1.0000 0.0273 -8.000 -0.5643 0.07453 0.06975 -0.0292 1.0000 0.0264 -7.750 -0.5643 0.06880 0.06395 -0.0333 1.0000 0.0255 -7.500 -0.5627 0.06311 0.05812 -0.0365 1.0000 0.0245 -7.250 -0.5589 0.05741 0.05220 -0.0386 1.0000 0.0236 -7.000 -0.5520 0.05204 0.04653 -0.0397 1.0000 0.0230 -6.750 -0.5410 0.04845 0.04271 -0.0400 1.0000 0.0240 -6.500 -0.5281 0.04503 0.03901 -0.0399 1.0000 0.0256 -6.250 -0.5141 0.04130 0.03491 -0.0394 1.0000 0.0266 -6.000 -0.4987 0.03755 0.03073 -0.0386 1.0000 0.0265 -5.750 -0.4815 0.03411 0.02684 -0.0375 1.0000 0.0265 -5.500 -0.4626 0.03108 0.02333 -0.0364 1.0000 0.0267 -5.250 -0.4423 0.02844 0.02023 -0.0352 1.0000 0.0272 -5.000 -0.4208 0.02647 0.01778 -0.0340 1.0000 0.0292 -4.750 -0.3985 0.02511 0.01599 -0.0328 1.0000 0.0312 -4.500 -0.3761 0.02330 0.01391 -0.0317 1.0000 0.0317 -4.250 -0.3539 0.02130 0.01175 -0.0307 1.0000 0.0327 -4.000 -0.3318 0.01991 0.01030 -0.0298 1.0000 0.0342 -3.750 -0.3097 0.01885 0.00919 -0.0289 1.0000 0.0362 -3.500 -0.2876 0.01799 0.00823 -0.0280 1.0000 0.0393 -3.250 -0.2652 0.01733 0.00747 -0.0272 1.0000 0.0450 -3.000 -0.2424 0.01657 0.00668 -0.0266 1.0000 0.0515 -2.750 -0.2166 0.01590 0.00593 -0.0265 0.9992 0.0623 -2.500 -0.1812 0.01463 0.00519 -0.0289 0.9949 0.1634 -2.250 -0.1547 0.01268 0.00514 -0.0294 0.9908 0.6248 -2.000 -0.1274 0.01240 0.00528 -0.0283 0.9847 0.7680 -1.750 -0.1041 0.01217 0.00533 -0.0255 0.9781 0.8724 -1.500 -0.0654 0.01211 0.00517 -0.0274 0.9726 0.9164 -1.250 -0.0197 0.01208 0.00496 -0.0313 0.9676 0.9461 -1.000 0.0281 0.01204 0.00477 -0.0359 0.9627 0.9775 -0.750 0.0709 0.01200 0.00460 -0.0396 0.9555 1.0000 -0.500 0.1061 0.01201 0.00447 -0.0417 0.9467 1.0000 -0.250 0.1425 0.01201 0.00439 -0.0438 0.9391 1.0000 0.000 0.1745 0.01204 0.00435 -0.0450 0.9289 1.0000 0.250 0.2069 0.01208 0.00434 -0.0462 0.9196 1.0000 0.500 0.2409 0.01210 0.00433 -0.0476 0.9114 1.0000 0.750 0.2702 0.01216 0.00438 -0.0481 0.9004 1.0000 1.000 0.3000 0.01223 0.00445 -0.0486 0.8900 1.0000 1.250 0.3301 0.01229 0.00455 -0.0491 0.8804 1.0000 1.500 0.3596 0.01235 0.00464 -0.0494 0.8705 1.0000 1.750 0.3871 0.01245 0.00480 -0.0494 0.8591 1.0000 2.000 0.4148 0.01255 0.00497 -0.0493 0.8478 1.0000 2.250 0.4425 0.01264 0.00518 -0.0492 0.8367 1.0000 2.500 0.4700 0.01273 0.00537 -0.0489 0.8249 1.0000 2.750 0.4965 0.01280 0.00556 -0.0484 0.8102 1.0000 3.000 0.5218 0.01274 0.00556 -0.0471 0.7867 1.0000 3.250 0.5432 0.01256 0.00534 -0.0442 0.7338 1.0000 3.500 0.5632 0.01260 0.00511 -0.0413 0.6509 1.0000 3.750 0.5838 0.01299 0.00514 -0.0391 0.5471 1.0000 4.000 0.5940 0.01496 0.00553 -0.0362 0.2461 1.0000 4.250 0.6099 0.01694 0.00655 -0.0349 0.0854 1.0000 4.500 0.6317 0.01801 0.00754 -0.0341 0.0573 1.0000 4.750 0.6537 0.01903 0.00862 -0.0331 0.0488 1.0000 5.000 0.6757 0.02003 0.00974 -0.0321 0.0438 1.0000 5.250 0.6965 0.02129 0.01104 -0.0310 0.0405 1.0000 5.500 0.7185 0.02257 0.01241 -0.0300 0.0368 1.0000 5.750 0.7420 0.02380 0.01378 -0.0293 0.0333 1.0000 6.250 0.7901 0.02725 0.01753 -0.0278 0.0299 1.0000 6.500 0.8138 0.02972 0.02016 -0.0272 0.0284 1.0000 6.750 0.8367 0.03196 0.02280 -0.0263 0.0262 1.0000 7.000 0.8585 0.03448 0.02581 -0.0251 0.0246 1.0000 7.250 0.8775 0.03768 0.02953 -0.0237 0.0239 1.0000 7.500 0.8932 0.04127 0.03365 -0.0220 0.0234 1.0000 7.750 0.9054 0.04512 0.03801 -0.0202 0.0230 1.0000 8.000 0.9150 0.04872 0.04206 -0.0186 0.0218 1.0000 8.250 0.9232 0.05180 0.04546 -0.0172 0.0204 1.0000 8.500 0.9304 0.05453 0.04845 -0.0161 0.0193 1.0000 8.750 0.9309 0.05847 0.05270 -0.0146 0.0190 1.0000 9.000 0.9262 0.06289 0.05744 -0.0130 0.0190 1.0000 9.250 0.9149 0.06769 0.06254 -0.0116 0.0191 1.0000 9.500 0.8965 0.07247 0.06754 -0.0104 0.0194 1.0000 9.750 0.8756 0.07794 0.07318 -0.0113 0.0198 1.0000 10.000 0.8547 0.08470 0.08001 -0.0149 0.0202 1.0000