XFOIL Version 6.96 Calculated polar for: S8037 (16%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.6881 0.14556 0.14331 -0.0269 1.0000 0.0058 -18.750 -0.7316 0.13211 0.12971 -0.0336 1.0000 0.0058 -18.500 -0.7663 0.12113 0.11862 -0.0391 1.0000 0.0058 -18.250 -0.8291 0.10537 0.10267 -0.0473 1.0000 0.0058 -18.000 -0.8807 0.09223 0.08936 -0.0542 1.0000 0.0057 -17.750 -0.9264 0.08042 0.07736 -0.0606 1.0000 0.0056 -17.500 -0.9525 0.07225 0.06904 -0.0652 1.0000 0.0057 -17.250 -0.9827 0.06384 0.06045 -0.0700 1.0000 0.0056 -17.000 -1.0069 0.05692 0.05337 -0.0737 1.0000 0.0057 -16.750 -1.0171 0.05243 0.04876 -0.0758 1.0000 0.0057 -16.500 -1.0267 0.04828 0.04450 -0.0774 1.0000 0.0057 -16.250 -1.0381 0.04420 0.04029 -0.0787 1.0000 0.0057 -16.000 -1.0419 0.04124 0.03723 -0.0793 1.0000 0.0057 -15.750 -1.0421 0.03879 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0.00149 -0.0356 0.5779 0.5185 -1.000 0.1235 0.00680 0.00148 -0.0348 0.5731 0.5531 -0.750 0.1488 0.00675 0.00147 -0.0342 0.5678 0.5728 -0.250 0.1985 0.00667 0.00146 -0.0329 0.5566 0.6181 0.000 0.2234 0.00665 0.00147 -0.0322 0.5499 0.6367 0.250 0.2487 0.00665 0.00148 -0.0317 0.5438 0.6497 0.500 0.2745 0.00665 0.00149 -0.0312 0.5377 0.6619 0.750 0.2997 0.00668 0.00150 -0.0306 0.5306 0.6738 1.000 0.3255 0.00668 0.00152 -0.0302 0.5242 0.6853 1.250 0.3506 0.00671 0.00155 -0.0296 0.5162 0.6953 1.500 0.3762 0.00674 0.00158 -0.0291 0.5085 0.7056 1.750 0.4010 0.00677 0.00161 -0.0284 0.5002 0.7160 2.000 0.4261 0.00681 0.00165 -0.0279 0.4926 0.7270 2.250 0.4503 0.00686 0.00170 -0.0271 0.4834 0.7399 2.500 0.4747 0.00688 0.00175 -0.0264 0.4755 0.7531 3.000 0.5226 0.00699 0.00187 -0.0248 0.4573 0.7787 3.250 0.5457 0.00706 0.00195 -0.0238 0.4470 0.7931 3.500 0.5681 0.00714 0.00203 -0.0227 0.4351 0.8090 3.750 0.5910 0.00719 0.00212 -0.0217 0.4244 0.8264 4.000 0.6133 0.00727 0.00222 -0.0206 0.4123 0.8460 4.250 0.6367 0.00735 0.00234 -0.0198 0.4000 0.8693 4.500 0.6653 0.00748 0.00249 -0.0201 0.3859 0.8958 4.750 0.7089 0.00770 0.00272 -0.0239 0.3708 0.9169 5.000 0.7608 0.00801 0.00297 -0.0296 0.3514 0.9296 5.250 0.8111 0.00832 0.00322 -0.0349 0.3350 0.9362 5.500 0.8509 0.00864 0.00348 -0.0378 0.3183 0.9447 5.750 0.8847 0.00903 0.00378 -0.0395 0.2972 0.9518 6.250 0.9291 0.00972 0.00431 -0.0377 0.2647 0.9729 6.500 0.9522 0.01006 0.00460 -0.0370 0.2498 0.9803 6.750 0.9768 0.01038 0.00486 -0.0367 0.2379 0.9847 7.000 1.0064 0.01070 0.00514 -0.0376 0.2264 0.9876 7.250 1.0340 0.01105 0.00543 -0.0380 0.2147 0.9908 7.500 1.0597 0.01139 0.00573 -0.0380 0.2038 0.9936 7.750 1.0899 0.01172 0.00602 -0.0391 0.1924 0.9953 8.000 1.1187 0.01208 0.00633 -0.0399 0.1812 0.9973 8.250 1.1462 0.01247 0.00666 -0.0405 0.1692 0.9992 8.500 1.1640 0.01278 0.00694 -0.0390 0.1602 1.0000 8.750 1.1687 0.01308 0.00722 -0.0347 0.1528 1.0000 9.000 1.1757 0.01342 0.00754 -0.0309 0.1458 1.0000 9.250 1.1843 0.01378 0.00789 -0.0276 0.1392 1.0000 9.500 1.1929 0.01420 0.00829 -0.0245 0.1322 1.0000 9.750 1.2030 0.01462 0.00871 -0.0217 0.1271 1.0000 10.000 1.2138 0.01507 0.00916 -0.0191 0.1218 1.0000 10.250 1.2218 0.01566 0.00973 -0.0162 0.1151 1.0000 10.500 1.2332 0.01618 0.01026 -0.0140 0.1104 1.0000 10.750 1.2423 0.01684 0.01091 -0.0116 0.1049 1.0000 11.000 1.2532 0.01748 0.01157 -0.0096 0.1008 1.0000 11.250 1.2641 0.01817 0.01227 -0.0077 0.0963 1.0000 11.500 1.2729 0.01903 0.01312 -0.0056 0.0913 1.0000 11.750 1.2838 0.01982 0.01393 -0.0040 0.0872 1.0000 12.000 1.2928 0.02078 0.01489 -0.0023 0.0824 1.0000 12.250 1.3022 0.02175 0.01587 -0.0007 0.0784 1.0000 12.500 1.3129 0.02269 0.01684 0.0007 0.0754 1.0000 12.750 1.3215 0.02379 0.01795 0.0021 0.0719 1.0000 13.000 1.3296 0.02497 0.01914 0.0035 0.0680 1.0000 13.250 1.3398 0.02603 0.02025 0.0046 0.0661 1.0000 13.500 1.3481 0.02726 0.02150 0.0058 0.0630 1.0000 13.750 1.3547 0.02864 0.02289 0.0070 0.0600 1.0000 14.000 1.3634 0.02989 0.02418 0.0080 0.0580 1.0000 14.250 1.3702 0.03131 0.02562 0.0091 0.0549 1.0000 14.500 1.3750 0.03293 0.02725 0.0101 0.0518 1.0000 14.750 1.3811 0.03447 0.02883 0.0110 0.0493 1.0000 15.000 1.3871 0.03607 0.03047 0.0119 0.0471 1.0000 15.250 1.3884 0.03810 0.03250 0.0128 0.0432 1.0000 15.500 1.3947 0.03976 0.03421 0.0134 0.0424 1.0000 15.750 1.3955 0.04195 0.03640 0.0142 0.0380 1.0000 16.000 1.4001 0.04385 0.03836 0.0147 0.0372 1.0000 16.250 1.4024 0.04601 0.04054 0.0152 0.0348 1.0000 16.500 1.4059 0.04809 0.04268 0.0155 0.0333 1.0000 16.750 1.4099 0.05018 0.04483 0.0158 0.0328 1.0000 17.000 1.4095 0.05275 0.04743 0.0160 0.0310 1.0000 17.250 1.4111 0.05515 0.04989 0.0162 0.0300 1.0000 17.500 1.4123 0.05763 0.05242 0.0163 0.0284 1.0000 17.750 1.4132 0.06020 0.05506 0.0162 0.0277 1.0000 18.000 1.4110 0.06318 0.05808 0.0161 0.0262 1.0000 18.250 1.4089 0.06616 0.06112 0.0159 0.0252 1.0000 18.500 1.4082 0.06901 0.06404 0.0156 0.0240 1.0000 18.750 1.4085 0.07184 0.06695 0.0153 0.0244 1.0000 19.000 1.4053 0.07511 0.07028 0.0148 0.0233 1.0000 19.250 1.3987 0.07885 0.07407 0.0141 0.0216 1.0000