XFOIL Version 6.96 Calculated polar for: Supermarine 371-II (tip) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5465 0.08194 0.07984 -0.0230 1.0000 0.0036 -8.500 -0.5526 0.07683 0.07478 -0.0277 1.0000 0.0035 -8.250 -0.5617 0.07226 0.07020 -0.0314 0.9771 0.0035 -8.000 -0.5541 0.06610 0.06387 -0.0381 0.9322 0.0033 -7.750 -0.5549 0.06181 0.05942 -0.0390 0.9078 0.0033 -7.500 -0.5553 0.05750 0.05493 -0.0391 0.8913 0.0032 -7.250 -0.5515 0.05340 0.05065 -0.0388 0.8789 0.0031 -7.000 -0.5463 0.04865 0.04567 -0.0382 0.8684 0.0030 -6.750 -0.5373 0.04439 0.04117 -0.0373 0.8598 0.0029 -6.500 -0.5263 0.03976 0.03624 -0.0361 0.8519 0.0029 -6.250 -0.5135 0.03497 0.03111 -0.0345 0.8453 0.0029 -6.000 -0.4983 0.03013 0.02586 -0.0326 0.8391 0.0029 -5.500 -0.4610 0.02100 0.01573 -0.0287 0.8293 0.0035 -5.250 -0.4380 0.01836 0.01268 -0.0276 0.8247 0.0039 -4.750 -0.3896 0.01509 0.00878 -0.0264 0.8167 0.0054 -4.500 -0.3648 0.01377 0.00727 -0.0257 0.8127 0.0058 -4.250 -0.3402 0.01273 0.00608 -0.0251 0.8091 0.0063 -4.000 -0.3156 0.01193 0.00516 -0.0245 0.8061 0.0077 -3.750 -0.2903 0.01133 0.00446 -0.0241 0.8027 0.0098 -3.500 -0.2637 0.01112 0.00421 -0.0241 0.7996 0.0119 -3.250 -0.2394 0.01040 0.00338 -0.0235 0.7966 0.0146 -3.000 -0.2133 0.01008 0.00298 -0.0233 0.7940 0.0167 -2.750 -0.1869 0.00979 0.00257 -0.0232 0.7914 0.0186 -2.500 -0.1601 0.00952 0.00220 -0.0231 0.7886 0.0202 -2.250 -0.1334 0.00926 0.00193 -0.0230 0.7859 0.0312 -2.000 -0.1072 0.00895 0.00174 -0.0229 0.7834 0.0736 -1.750 -0.0822 0.00846 0.00156 -0.0228 0.7810 0.1725 -1.500 -0.0697 0.00645 0.00129 -0.0209 0.7783 0.6810 -1.250 -0.0464 0.00623 0.00141 -0.0197 0.7758 0.7579 -1.000 -0.0194 0.00627 0.00143 -0.0196 0.7734 0.7831 -0.750 0.0076 0.00628 0.00144 -0.0194 0.7713 0.8002 -0.500 0.0351 0.00628 0.00142 -0.0194 0.7693 0.8101 -0.250 0.0631 0.00629 0.00139 -0.0195 0.7675 0.8143 0.000 0.0912 0.00630 0.00137 -0.0198 0.7657 0.8184 0.250 0.1193 0.00629 0.00138 -0.0200 0.7633 0.8219 0.500 0.1473 0.00628 0.00140 -0.0201 0.7612 0.8254 0.750 0.1754 0.00629 0.00143 -0.0203 0.7592 0.8293 1.250 0.2315 0.00632 0.00152 -0.0207 0.7553 0.8367 1.500 0.2592 0.00633 0.00157 -0.0208 0.7519 0.8408 1.750 0.2865 0.00630 0.00160 -0.0207 0.7421 0.8454 2.000 0.3125 0.00624 0.00153 -0.0202 0.7180 0.8497 2.250 0.3381 0.00623 0.00146 -0.0197 0.6793 0.8543 2.500 0.3560 0.00699 0.00149 -0.0179 0.4839 0.8598 2.750 0.3691 0.00873 0.00209 -0.0161 0.1853 0.8658 3.000 0.3912 0.00941 0.00243 -0.0156 0.0812 0.8719 3.250 0.4151 0.00985 0.00273 -0.0151 0.0348 0.8778 3.500 0.4400 0.01018 0.00309 -0.0146 0.0240 0.8844 3.750 0.4652 0.01041 0.00342 -0.0143 0.0208 0.8914 4.000 0.4895 0.01077 0.00381 -0.0138 0.0154 0.8998 4.250 0.5141 0.01105 0.00419 -0.0133 0.0128 0.9084 4.500 0.5380 0.01147 0.00470 -0.0126 0.0096 0.9182 4.750 0.5609 0.01213 0.00551 -0.0118 0.0072 0.9300 5.000 0.5849 0.01291 0.00641 -0.0113 0.0056 0.9434 5.250 0.6126 0.01378 0.00741 -0.0116 0.0048 0.9572 5.500 0.6423 0.01501 0.00880 -0.0123 0.0041 0.9716 5.750 0.6725 0.01665 0.01063 -0.0130 0.0037 0.9892 6.000 0.6985 0.01864 0.01288 -0.0127 0.0035 1.0000 6.250 0.7204 0.02129 0.01586 -0.0114 0.0034 1.0000 6.500 0.7395 0.02517 0.02021 -0.0094 0.0035 1.0000 6.750 0.7545 0.03026 0.02582 -0.0066 0.0037 1.0000 7.000 0.7666 0.03515 0.03113 -0.0040 0.0039 1.0000 7.250 0.7764 0.03981 0.03614 -0.0015 0.0041 1.0000 7.500 0.7833 0.04451 0.04115 0.0009 0.0043 1.0000 7.750 0.7881 0.04891 0.04581 0.0029 0.0045 1.0000 8.000 0.7917 0.05315 0.05026 0.0046 0.0045 1.0000 8.250 0.7934 0.05732 0.05461 0.0062 0.0042 1.0000 8.500 0.7921 0.06126 0.05871 0.0075 0.0040 1.0000 8.750 0.7799 0.06593 0.06352 0.0089 0.0046 1.0000 9.000 0.7726 0.06900 0.06667 0.0104 0.0038 1.0000 9.250 0.7558 0.07293 0.07068 0.0108 0.0039 1.0000 9.500 0.7440 0.07688 0.07469 0.0095 0.0036 1.0000 9.750 0.7246 0.08370 0.08155 0.0052 0.0040 1.0000