XFOIL Version 6.96 Calculated polar for: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.5615 0.08737 0.08376 -0.0332 1.0000 0.0133 -10.250 -0.5754 0.07988 0.07633 -0.0374 1.0000 0.0132 -10.000 -0.5965 0.06897 0.06548 -0.0459 1.0000 0.0127 -9.750 -0.6257 0.06082 0.05722 -0.0503 1.0000 0.0124 -9.500 -0.6561 0.05558 0.05184 -0.0490 1.0000 0.0122 -9.250 -0.6856 0.05146 0.04755 -0.0445 1.0000 0.0120 -9.000 -0.7112 0.04658 0.04236 -0.0399 1.0000 0.0117 -8.750 -0.7261 0.04281 0.03828 -0.0354 1.0000 0.0117 -8.500 -0.7356 0.03939 0.03451 -0.0309 1.0000 0.0116 -8.250 -0.7395 0.03651 0.03130 -0.0268 1.0000 0.0116 -8.000 -0.7394 0.03399 0.02845 -0.0229 1.0000 0.0118 -7.750 -0.7359 0.03171 0.02585 -0.0193 1.0000 0.0119 -7.500 -0.7294 0.02970 0.02354 -0.0160 1.0000 0.0122 -7.250 -0.7208 0.02776 0.02129 -0.0129 1.0000 0.0124 -7.000 -0.7070 0.02603 0.01924 -0.0107 0.9995 0.0128 -6.750 -0.6792 0.02410 0.01698 -0.0112 0.9964 0.0134 -6.500 -0.6504 0.02252 0.01511 -0.0118 0.9934 0.0142 -6.250 -0.6211 0.02152 0.01387 -0.0124 0.9897 0.0156 -6.000 -0.5931 0.01990 0.01209 -0.0129 0.9863 0.0167 -5.750 -0.5632 0.01866 0.01077 -0.0138 0.9832 0.0180 -5.500 -0.5357 0.01773 0.00972 -0.0141 0.9787 0.0193 -5.250 -0.5068 0.01691 0.00879 -0.0145 0.9741 0.0210 -5.000 -0.4751 0.01620 0.00795 -0.0156 0.9705 0.0238 -4.750 -0.4470 0.01544 0.00716 -0.0160 0.9657 0.0292 -4.500 -0.4182 0.01481 0.00645 -0.0163 0.9604 0.0358 -4.250 -0.3867 0.01411 0.00585 -0.0175 0.9568 0.0603 -4.000 -0.3586 0.01352 0.00544 -0.0179 0.9517 0.1032 -3.750 -0.3302 0.01302 0.00509 -0.0183 0.9462 0.1466 -3.500 -0.2991 0.01238 0.00473 -0.0195 0.9426 0.2123 -3.250 -0.2764 0.01158 0.00440 -0.0190 0.9360 0.3238 -3.000 -0.2531 0.01078 0.00414 -0.0184 0.9301 0.4591 -2.750 -0.2289 0.01021 0.00397 -0.0177 0.9245 0.5655 -2.500 -0.2048 0.00983 0.00385 -0.0167 0.9176 0.6422 -2.250 -0.1736 0.00953 0.00374 -0.0171 0.9136 0.7109 -2.000 -0.1463 0.00939 0.00373 -0.0166 0.9063 0.7626 -1.750 -0.1111 0.00931 0.00370 -0.0178 0.9016 0.8051 -1.500 -0.0747 0.00930 0.00370 -0.0192 0.8967 0.8371 -1.250 -0.0382 0.00936 0.00375 -0.0206 0.8903 0.8689 -1.000 0.0041 0.00948 0.00387 -0.0231 0.8861 0.8978 -0.750 0.0405 0.00958 0.00393 -0.0246 0.8786 0.9130 -0.500 0.0823 0.00963 0.00392 -0.0274 0.8725 0.9203 -0.250 0.1157 0.00966 0.00391 -0.0284 0.8634 0.9286 0.000 0.1557 0.00967 0.00387 -0.0310 0.8556 0.9332 0.250 0.1867 0.00969 0.00385 -0.0315 0.8449 0.9410 0.500 0.2254 0.00971 0.00385 -0.0338 0.8342 0.9442 0.750 0.2610 0.00972 0.00384 -0.0354 0.8223 0.9489 1.000 0.2912 0.00974 0.00384 -0.0358 0.8088 0.9553 1.250 0.3280 0.00975 0.00382 -0.0377 0.7937 0.9585 1.500 0.3619 0.00978 0.00381 -0.0389 0.7766 0.9629 1.750 0.3909 0.00983 0.00385 -0.0390 0.7592 0.9689 2.000 0.4264 0.00986 0.00387 -0.0407 0.7408 0.9721 2.250 0.4597 0.00991 0.00391 -0.0419 0.7215 0.9763 2.500 0.4894 0.01000 0.00396 -0.0423 0.6985 0.9814 2.750 0.5223 0.01008 0.00399 -0.0434 0.6664 0.9850 3.000 0.5543 0.01019 0.00403 -0.0443 0.6338 0.9891 3.250 0.5847 0.01035 0.00413 -0.0450 0.6000 0.9935 3.500 0.6160 0.01055 0.00421 -0.0459 0.5574 0.9973 3.750 0.6408 0.01089 0.00435 -0.0455 0.4940 1.0000 4.000 0.6533 0.01141 0.00451 -0.0426 0.4099 1.0000 4.250 0.6645 0.01211 0.00478 -0.0397 0.3200 1.0000 4.500 0.6765 0.01285 0.00514 -0.0370 0.2402 1.0000 4.750 0.6888 0.01363 0.00555 -0.0345 0.1645 1.0000 5.000 0.7016 0.01441 0.00605 -0.0320 0.1053 1.0000 5.250 0.7155 0.01511 0.00655 -0.0296 0.0659 1.0000 5.500 0.7299 0.01579 0.00711 -0.0273 0.0435 1.0000 5.750 0.7452 0.01639 0.00771 -0.0250 0.0334 1.0000 6.000 0.7596 0.01708 0.00844 -0.0225 0.0283 1.0000 6.250 0.7747 0.01770 0.00917 -0.0202 0.0250 1.0000 6.500 0.7889 0.01839 0.00989 -0.0178 0.0220 1.0000 6.750 0.8013 0.01924 0.01085 -0.0151 0.0198 1.0000 7.000 0.8150 0.02004 0.01175 -0.0126 0.0186 1.0000 7.250 0.8285 0.02091 0.01273 -0.0100 0.0175 1.0000 7.500 0.8420 0.02187 0.01376 -0.0076 0.0164 1.0000 7.750 0.8560 0.02285 0.01481 -0.0053 0.0155 1.0000 8.000 0.8688 0.02405 0.01606 -0.0030 0.0143 1.0000 8.250 0.8833 0.02531 0.01745 -0.0010 0.0132 1.0000 8.500 0.8987 0.02659 0.01890 0.0010 0.0127 1.0000 8.750 0.9136 0.02814 0.02069 0.0030 0.0120 1.0000 9.000 0.9276 0.02982 0.02259 0.0051 0.0115 1.0000 9.250 0.9396 0.03161 0.02462 0.0073 0.0112 1.0000 9.500 0.9490 0.03356 0.02683 0.0099 0.0108 1.0000 9.750 0.9556 0.03566 0.02921 0.0127 0.0106 1.0000 10.000 0.9589 0.03779 0.03161 0.0157 0.0104 1.0000 10.250 0.9570 0.03991 0.03398 0.0194 0.0102 1.0000 10.500 0.9508 0.04220 0.03651 0.0234 0.0101 1.0000 10.750 0.9444 0.04432 0.03885 0.0269 0.0100 1.0000 11.000 0.9332 0.04710 0.04187 0.0301 0.0100 1.0000 11.250 0.9283 0.04887 0.04372 0.0320 0.0096 1.0000 11.500 0.9154 0.05195 0.04700 0.0338 0.0095 1.0000 11.750 0.8997 0.05557 0.05079 0.0347 0.0093 1.0000 12.000 0.8841 0.05960 0.05503 0.0346 0.0094 1.0000 12.250 0.8651 0.06460 0.06025 0.0333 0.0094 1.0000 12.500 0.8456 0.07024 0.06603 0.0307 0.0093 1.0000 12.750 0.7705 0.09116 0.08750 0.0171 0.0108 1.0000