XFOIL Version 6.94 Calculated polar for: EPPLER 393 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 0.5298 0.00937 0.00349 -0.1212 0.6975 0.7449 0.500 0.5829 0.00943 0.00358 -0.1204 0.6858 0.7932 1.000 0.6315 0.00942 0.00373 -0.1185 0.6736 0.8499 1.500 0.6743 0.00937 0.00374 -0.1151 0.6629 0.9393 2.000 0.7383 0.00947 0.00383 -0.1172 0.6506 1.0000 2.500 0.7965 0.00978 0.00404 -0.1180 0.6391 1.0000 3.000 0.8530 0.01001 0.00425 -0.1183 0.6260 1.0000 3.500 0.9083 0.01027 0.00451 -0.1183 0.6118 1.0000 4.000 0.9633 0.01053 0.00476 -0.1182 0.5973 1.0000 4.500 1.0179 0.01079 0.00501 -0.1180 0.5816 1.0000 5.000 1.0701 0.01098 0.00530 -0.1173 0.5634 1.0000 5.500 1.1218 0.01121 0.00562 -0.1165 0.5439 1.0000 6.000 1.1719 0.01150 0.00596 -0.1154 0.5205 1.0000 6.500 1.2197 0.01179 0.00639 -0.1139 0.4908 1.0000 7.000 1.2619 0.01229 0.00685 -0.1114 0.4427 1.0000 7.500 1.2900 0.01352 0.00766 -0.1066 0.3455 1.0000 8.000 1.3010 0.01582 0.00929 -0.0996 0.2280 1.0000 8.500 1.3108 0.01786 0.01094 -0.0925 0.1567 1.0000 9.000 1.3216 0.01986 0.01274 -0.0859 0.1096 1.0000 9.500 1.3302 0.02217 0.01487 -0.0797 0.0710 1.0000 10.000 1.3367 0.02488 0.01746 -0.0742 0.0418 1.0000 10.500 1.3358 0.02852 0.02102 -0.0687 0.0194 1.0000 11.000 1.3292 0.03323 0.02584 -0.0639 0.0107 1.0000 11.500 1.3287 0.03793 0.03077 -0.0607 0.0090 1.0000 12.000 1.3292 0.04297 0.03604 -0.0585 0.0081 1.0000 12.500 1.3235 0.04908 0.04232 -0.0570 0.0075 1.0000 13.000 1.3228 0.05513 0.04860 -0.0561 0.0072 1.0000 13.500 1.3246 0.06132 0.05504 -0.0556 0.0070 1.0000 14.000 1.3285 0.06766 0.06164 -0.0555 0.0068 1.0000 14.500 1.3330 0.07434 0.06862 -0.0558 0.0066 1.0000 15.000 1.3340 0.08198 0.07663 -0.0568 0.0066 1.0000 15.500 1.3277 0.09116 0.08623 -0.0590 0.0066 1.0000 16.000 1.3137 0.10206 0.09759 -0.0628 0.0067 1.0000 16.500 1.2934 0.11460 0.11057 -0.0684 0.0068 1.0000 17.000 1.2694 0.12858 0.12496 -0.0760 0.0069 1.0000 17.500 1.2442 0.14365 0.14039 -0.0852 0.0071 1.0000 18.000 1.2195 0.15964 0.15668 -0.0957 0.0072 1.0000 18.500 1.1962 0.17627 0.17355 -0.1069 0.0074 1.0000 20.500 0.9375 0.28301 0.28119 -0.1543 0.0197 1.0000 21.000 0.9346 0.29709 0.29525 -0.1608 0.0185 1.0000 21.500 0.9426 0.30620 0.30440 -0.1641 0.0172 1.0000 22.000 0.9503 0.31583 0.31404 -0.1673 0.0167 1.0000 22.500 0.9540 0.32806 0.32627 -0.1720 0.0153 1.0000 23.000 0.9614 0.33726 0.33551 -0.1752 0.0145 1.0000 23.500 0.9669 0.34876 0.34702 -0.1790 0.0138 1.0000 24.000 0.9733 0.35889 0.35717 -0.1824 0.0122 1.0000 24.500 0.9808 0.36809 0.36640 -0.1850 0.0117 1.0000 25.000 0.9846 0.38132 0.37963 -0.1894 0.0106 1.0000 25.500 0.9907 0.39121 0.38955 -0.1925 0.0097 1.0000 26.000 0.9954 0.40335 0.40170 -0.1959 0.0093 1.0000 26.500 1.0005 0.41492 0.41328 -0.1993 0.0086 1.0000 27.000 1.0055 0.42588 0.42427 -0.2024 0.0081 1.0000 27.500 1.0102 0.43589 0.43431 -0.2053 0.0076 1.0000 28.000 1.0144 0.44738 0.44581 -0.2083 0.0074 1.0000 28.500 1.0181 0.45996 0.45842 -0.2118 0.0072 1.0000 29.000 1.0218 0.47150 0.46998 -0.2148 0.0068 1.0000 29.500 1.0253 0.48288 0.48138 -0.2179 0.0064 1.0000 30.000 1.0283 0.49416 0.49269 -0.2208 0.0060 1.0000 30.500 1.0308 0.50476 0.50332 -0.2236 0.0057 1.0000 31.000 1.0330 0.51522 0.51382 -0.2263 0.0056 1.0000 32.000 1.0364 0.53869 0.53733 -0.2321 0.0055 1.0000 32.500 1.0380 0.55051 0.54918 -0.2350 0.0054 1.0000 33.000 1.0393 0.56218 0.56087 -0.2378 0.0053 1.0000 33.500 1.0402 0.57350 0.57222 -0.2405 0.0050 1.0000 34.000 1.0406 0.58461 0.58336 -0.2432 0.0049 1.0000 34.500 1.0407 0.59573 0.59452 -0.2458 0.0046 1.0000 35.000 1.0403 0.60654 0.60536 -0.2484 0.0044 1.0000 35.500 1.0395 0.61692 0.61577 -0.2509 0.0043 1.0000 36.000 1.0378 0.62669 0.62558 -0.2534 0.0040 1.0000 37.000 1.0348 0.64887 0.64779 -0.2583 0.0039 1.0000 37.500 1.0329 0.65930 0.65826 -0.2607 0.0038 1.0000 38.000 1.0314 0.67063 0.66961 -0.2630 0.0036 1.0000 38.500 1.0289 0.68120 0.68021 -0.2652 0.0033 1.0000 39.000 1.0260 0.69089 0.68993 -0.2675 0.0032 1.0000 39.500 1.0227 0.70050 0.69956 -0.2697 0.0031 1.0000 40.000 1.0190 0.70980 0.70890 -0.2719 0.0029 1.0000 40.500 1.0149 0.71878 0.71791 -0.2740 0.0027 1.0000 41.000 1.0105 0.72746 0.72661 -0.2761 0.0026 1.0000 41.500 1.0058 0.73573 0.73492 -0.2782 0.0026 1.0000 42.000 1.0005 0.74352 0.74273 -0.2802 0.0026 1.0000