XFOIL Version 6.94 Calculated polar for: EPPLER STE 87(-3)-914 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4478 0.02077 0.01589 -0.1243 0.8360 0.8037 0.500 0.5169 0.01965 0.01477 -0.1252 0.8314 0.8213 1.500 0.6317 0.01806 0.01320 -0.1241 0.8133 0.8492 3.000 0.7632 0.01521 0.01055 -0.1132 0.7751 0.9050 3.500 0.8208 0.01411 0.00945 -0.1127 0.7553 0.9154 4.000 0.8866 0.01322 0.00851 -0.1142 0.7215 0.9209 4.500 0.9570 0.01267 0.00772 -0.1167 0.6697 0.9244 5.000 1.0018 0.01319 0.00791 -0.1150 0.6011 0.9288 5.500 1.0265 0.01418 0.00854 -0.1097 0.5308 0.9340 6.000 1.0457 0.01554 0.00951 -0.1039 0.4554 0.9409 6.500 1.0698 0.01702 0.01066 -0.0995 0.3895 0.9465 7.500 1.1271 0.01951 0.01275 -0.0923 0.3011 0.9660 8.000 1.1647 0.02051 0.01373 -0.0905 0.2779 0.9981 8.500 1.2059 0.02180 0.01498 -0.0896 0.2505 0.9981 9.000 1.2452 0.02316 0.01634 -0.0885 0.2284 0.9981 9.500 1.2812 0.02469 0.01780 -0.0870 0.1992 0.9981 10.000 1.3141 0.02643 0.01944 -0.0851 0.1650 0.9981 10.500 1.3258 0.02962 0.02205 -0.0808 0.0829 0.9981 11.000 1.3235 0.03401 0.02599 -0.0751 0.0182 0.9981 11.500 1.3363 0.03740 0.02945 -0.0714 0.0075 0.9981 12.000 1.3522 0.04063 0.03288 -0.0683 0.0062 0.9981 12.500 1.3654 0.04420 0.03668 -0.0654 0.0056 0.9981 13.000 1.3727 0.04845 0.04117 -0.0626 0.0053 0.9981 13.500 1.3712 0.05384 0.04683 -0.0599 0.0050 0.9981 14.000 1.3670 0.05989 0.05315 -0.0579 0.0050 0.9981 14.500 1.3573 0.06703 0.06056 -0.0568 0.0049 0.9981 15.000 1.3429 0.07525 0.06906 -0.0567 0.0049 0.9981 15.500 1.3247 0.08446 0.07855 -0.0577 0.0048 0.9981 16.000 1.3051 0.09436 0.08872 -0.0597 0.0048 0.9981 16.500 1.2857 0.10446 0.09906 -0.0624 0.0048 0.9981 17.000 1.2696 0.11424 0.10905 -0.0655 0.0048 0.9981 17.500 1.2578 0.12334 0.11834 -0.0686 0.0048 0.9981 18.000 1.2508 0.13159 0.12676 -0.0717 0.0048 0.9981 18.500 1.2473 0.13921 0.13455 -0.0747 0.0048 0.9981 19.000 1.2465 0.14642 0.14192 -0.0779 0.0049 0.9981 19.500 1.2461 0.15364 0.14933 -0.0814 0.0049 0.9981 20.000 1.2436 0.16149 0.15739 -0.0856 0.0049 0.9981 20.500 1.2396 0.16992 0.16605 -0.0906 0.0050 0.9981 21.000 1.2334 0.17917 0.17553 -0.0966 0.0050 0.9981 21.500 1.2246 0.19013 0.18677 -0.1044 0.0051 0.9981 22.000 1.2000 0.20682 0.20393 -0.1164 0.0054 0.9981 22.500 1.1200 0.24985 0.24752 -0.1432 0.0070 0.9981