XFOIL Version 6.96 Calculated polar for: EPPLER 68 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4338 0.09856 0.09537 -0.0398 1.0000 0.0645 -9.250 -0.4451 0.09602 0.09289 -0.0386 1.0000 0.0652 -9.000 -0.5775 0.06158 0.05825 -0.0669 0.9905 0.0372 -8.750 -0.5845 0.05349 0.04982 -0.0742 0.9828 0.0354 -8.500 -0.6074 0.04086 0.03572 -0.0789 0.9719 0.0307 -8.250 -0.5929 0.03809 0.03256 -0.0788 0.9654 0.0305 -8.000 -0.5703 0.03462 0.02864 -0.0803 0.9612 0.0305 -7.750 -0.5437 0.03084 0.02452 -0.0825 0.9588 0.0316 -7.500 -0.5246 0.02936 0.02291 -0.0819 0.9525 0.0328 -7.250 -0.4952 0.02772 0.02105 -0.0830 0.9487 0.0340 -7.000 -0.4614 0.02595 0.01900 -0.0847 0.9462 0.0350 -6.750 -0.4327 0.02456 0.01742 -0.0852 0.9423 0.0364 -6.500 -0.4079 0.02346 0.01616 -0.0849 0.9367 0.0378 -6.250 -0.3760 0.02189 0.01451 -0.0862 0.9336 0.0406 -6.000 -0.3392 0.02102 0.01362 -0.0883 0.9315 0.0465 -5.750 -0.3185 0.02010 0.01269 -0.0874 0.9250 0.0539 -5.500 -0.2879 0.01904 0.01166 -0.0883 0.9208 0.0747 -5.250 -0.2514 0.01826 0.01097 -0.0905 0.9183 0.1033 -5.000 -0.2123 0.01765 0.01046 -0.0931 0.9164 0.1340 -4.750 -0.1945 0.01740 0.01029 -0.0916 0.9083 0.1618 -4.500 -0.1587 0.01687 0.00989 -0.0935 0.9052 0.2031 -4.250 -0.1201 0.01629 0.00946 -0.0959 0.9031 0.2482 -4.000 -0.0797 0.01574 0.00906 -0.0987 0.9016 0.2996 -3.750 -0.0636 0.01561 0.00903 -0.0966 0.8927 0.3378 -3.500 -0.0259 0.01517 0.00876 -0.0987 0.8902 0.3923 -3.250 0.0146 0.01476 0.00847 -0.1012 0.8885 0.4465 -3.000 0.0548 0.01439 0.00822 -0.1035 0.8869 0.4955 -2.750 0.0719 0.01440 0.00830 -0.1014 0.8779 0.5292 -2.500 0.1087 0.01411 0.00807 -0.1030 0.8751 0.5683 -2.250 0.1472 0.01380 0.00783 -0.1048 0.8730 0.6052 -2.000 0.1681 0.01381 0.00790 -0.1033 0.8652 0.6343 -1.750 0.2016 0.01359 0.00773 -0.1040 0.8613 0.6654 -1.500 0.2382 0.01334 0.00751 -0.1053 0.8587 0.6956 -1.250 0.2603 0.01336 0.00758 -0.1039 0.8512 0.7215 -1.000 0.2916 0.01319 0.00744 -0.1042 0.8465 0.7485 -0.750 0.3265 0.01296 0.00724 -0.1050 0.8434 0.7726 -0.500 0.3455 0.01303 0.00735 -0.1029 0.8349 0.7960 -0.250 0.3762 0.01284 0.00718 -0.1029 0.8304 0.8182 0.000 0.4008 0.01279 0.00715 -0.1018 0.8243 0.8410 0.250 0.4236 0.01272 0.00711 -0.1001 0.8174 0.8621 0.500 0.4544 0.01252 0.00688 -0.1000 0.8134 0.8842 0.750 0.4690 0.01254 0.00695 -0.0968 0.8041 0.9069 1.000 0.5003 0.01233 0.00672 -0.0969 0.7995 0.9290 1.250 0.5301 0.01231 0.00672 -0.0970 0.7911 0.9498 1.500 0.5772 0.01215 0.00651 -0.1007 0.7858 0.9651 1.750 0.6241 0.01209 0.00645 -0.1046 0.7782 0.9787 2.000 0.6766 0.01194 0.00626 -0.1097 0.7713 0.9882 2.250 0.7253 0.01187 0.00619 -0.1142 0.7625 1.0000 2.500 0.7482 0.01177 0.00603 -0.1134 0.7547 1.0000 2.750 0.7579 0.01184 0.00610 -0.1102 0.7438 1.0000 3.000 0.7783 0.01188 0.00610 -0.1088 0.7342 1.0000 3.250 0.8065 0.01185 0.00602 -0.1089 0.7254 1.0000 3.500 0.8276 0.01193 0.00611 -0.1076 0.7139 1.0000 3.750 0.8520 0.01200 0.00616 -0.1069 0.7029 1.0000 4.000 0.8787 0.01205 0.00618 -0.1066 0.6923 1.0000 4.250 0.9057 0.01210 0.00620 -0.1064 0.6811 1.0000 4.500 0.9288 0.01220 0.00632 -0.1054 0.6682 1.0000 4.750 0.9526 0.01230 0.00643 -0.1045 0.6548 1.0000 5.000 0.9763 0.01241 0.00654 -0.1037 0.6410 1.0000 5.250 0.9998 0.01254 0.00667 -0.1027 0.6265 1.0000 5.500 1.0228 0.01268 0.00681 -0.1017 0.6112 1.0000 5.750 1.0453 0.01283 0.00695 -0.1006 0.5948 1.0000 6.000 1.0675 0.01302 0.00710 -0.0994 0.5778 1.0000 6.250 1.0874 0.01323 0.00734 -0.0978 0.5590 1.0000 6.500 1.1067 0.01347 0.00757 -0.0962 0.5388 1.0000 6.750 1.1256 0.01375 0.00780 -0.0944 0.5180 1.0000 7.000 1.1418 0.01406 0.00809 -0.0922 0.4941 1.0000 7.250 1.1570 0.01442 0.00841 -0.0898 0.4691 1.0000 7.500 1.1704 0.01486 0.00878 -0.0872 0.4426 1.0000 7.750 1.1811 0.01534 0.00918 -0.0841 0.4149 1.0000 8.000 1.1897 0.01588 0.00964 -0.0807 0.3864 1.0000 8.250 1.1970 0.01654 0.01019 -0.0772 0.3564 1.0000 8.500 1.2028 0.01731 0.01083 -0.0736 0.3240 1.0000 8.750 1.2072 0.01822 0.01158 -0.0700 0.2896 1.0000 9.000 1.2103 0.01927 0.01245 -0.0664 0.2555 1.0000 9.250 1.2136 0.02041 0.01343 -0.0631 0.2232 1.0000 9.500 1.2180 0.02159 0.01447 -0.0602 0.1934 1.0000 9.750 1.2230 0.02283 0.01559 -0.0574 0.1682 1.0000 10.000 1.2291 0.02408 0.01675 -0.0550 0.1452 1.0000 10.250 1.2333 0.02550 0.01807 -0.0525 0.1254 1.0000 10.500 1.2391 0.02689 0.01941 -0.0503 0.1063 1.0000 10.750 1.2423 0.02853 0.02096 -0.0479 0.0889 1.0000 11.000 1.2437 0.03037 0.02272 -0.0456 0.0740 1.0000 11.250 1.2445 0.03236 0.02471 -0.0433 0.0599 1.0000 11.500 1.2417 0.03473 0.02705 -0.0410 0.0499 1.0000 11.750 1.2418 0.03696 0.02930 -0.0390 0.0435 1.0000 12.000 1.2408 0.03938 0.03179 -0.0372 0.0393 1.0000 12.250 1.2445 0.04145 0.03394 -0.0358 0.0361 1.0000 12.500 1.2444 0.04394 0.03644 -0.0344 0.0338 1.0000 12.750 1.2464 0.04639 0.03896 -0.0331 0.0318 1.0000 13.000 1.2525 0.04849 0.04119 -0.0321 0.0302 1.0000 13.250 1.2585 0.05066 0.04347 -0.0311 0.0289 1.0000 13.500 1.2645 0.05288 0.04575 -0.0303 0.0277 1.0000 13.750 1.2714 0.05511 0.04806 -0.0295 0.0268 1.0000 14.000 1.2839 0.05750 0.05046 -0.0283 0.0255 1.0000 14.250 1.2904 0.05996 0.05311 -0.0277 0.0249 1.0000 14.500 1.2941 0.06259 0.05594 -0.0272 0.0242 1.0000 14.750 1.2968 0.06543 0.05897 -0.0269 0.0234 1.0000 15.000 1.2988 0.06842 0.06215 -0.0267 0.0227 1.0000 15.250 1.3000 0.07174 0.06567 -0.0265 0.0224 1.0000 15.500 1.2987 0.07534 0.06947 -0.0266 0.0220 1.0000 15.750 1.2951 0.07933 0.07366 -0.0269 0.0217 1.0000 16.000 1.2889 0.08371 0.07825 -0.0276 0.0215 1.0000 16.250 1.2804 0.08852 0.08329 -0.0287 0.0213 1.0000 16.500 1.2694 0.09384 0.08883 -0.0303 0.0213 1.0000 16.750 1.2560 0.09972 0.09495 -0.0324 0.0212 1.0000 17.000 1.2397 0.10629 0.10176 -0.0352 0.0213 1.0000 17.250 1.2168 0.11439 0.11015 -0.0393 0.0215 1.0000 17.500 1.1907 0.12359 0.11963 -0.0446 0.0217 1.0000 17.750 1.1611 0.13426 0.13057 -0.0513 0.0221 1.0000 18.000 1.1261 0.14724 0.14381 -0.0600 0.0227 1.0000 18.250 1.0817 0.16434 0.16112 -0.0717 0.0236 1.0000 18.500 1.0387 0.18344 0.18028 -0.0835 0.0249 1.0000