XFOIL Version 6.96 Calculated polar for: EPPLER 332 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.3107 0.08709 0.08473 -0.0174 0.8271 0.0108 -9.250 -0.3135 0.08280 0.08032 -0.0188 0.7961 0.0108 -5.750 -0.3776 0.03691 0.03236 -0.0225 0.6287 0.0084 -5.250 -0.3529 0.02854 0.02328 -0.0169 0.6080 0.0056 -5.000 -0.3372 0.02543 0.01979 -0.0146 0.5975 0.0054 -4.750 -0.3184 0.02277 0.01676 -0.0126 0.5867 0.0053 -4.500 -0.2978 0.02020 0.01377 -0.0108 0.5766 0.0051 -4.000 -0.2497 0.01649 0.00933 -0.0083 0.5557 0.0049 -3.750 -0.2242 0.01524 0.00781 -0.0075 0.5459 0.0049 -3.250 -0.1737 0.01357 0.00579 -0.0059 0.5265 0.0051 -3.000 -0.1487 0.01306 0.00516 -0.0052 0.5172 0.0051 -2.750 -0.1240 0.01259 0.00460 -0.0045 0.5079 0.0052 -2.500 -0.0991 0.01217 0.00408 -0.0037 0.4999 0.0054 -2.250 -0.0741 0.01186 0.00369 -0.0030 0.4914 0.0056 -2.000 -0.0491 0.01152 0.00329 -0.0023 0.4833 0.0060 -1.750 -0.0237 0.01131 0.00301 -0.0017 0.4752 0.0069 -1.500 0.0022 0.01112 0.00276 -0.0012 0.4679 0.0079 -1.000 0.0535 0.01075 0.00236 -0.0002 0.4540 0.0197 -0.750 0.0779 0.01047 0.00223 0.0005 0.4470 0.0653 -0.500 0.1006 0.01000 0.00213 0.0014 0.4406 0.1776 -0.250 0.0904 0.00762 0.00224 0.0092 0.4363 0.8652 0.250 0.1381 0.00799 0.00249 0.0118 0.4247 0.9167 0.500 0.1641 0.00829 0.00272 0.0129 0.4184 0.9317 0.750 0.2055 0.00867 0.00303 0.0106 0.4119 0.9404 1.000 0.2347 0.00887 0.00315 0.0106 0.4060 0.9479 1.250 0.2674 0.00897 0.00316 0.0096 0.4003 0.9491 1.500 0.2972 0.00900 0.00314 0.0092 0.3945 0.9499 1.750 0.3264 0.00906 0.00313 0.0088 0.3889 0.9509 2.000 0.3550 0.00912 0.00313 0.0086 0.3841 0.9520 2.250 0.3833 0.00917 0.00314 0.0085 0.3785 0.9531 2.500 0.4106 0.00923 0.00315 0.0085 0.3733 0.9545 2.750 0.4368 0.00928 0.00317 0.0088 0.3688 0.9559 3.000 0.4617 0.00933 0.00319 0.0093 0.3637 0.9577 3.250 0.4825 0.00938 0.00321 0.0108 0.3591 0.9602 3.500 0.5071 0.00944 0.00324 0.0113 0.3547 0.9615 3.750 0.5364 0.00950 0.00330 0.0109 0.3497 0.9621 4.000 0.5655 0.00959 0.00336 0.0105 0.3445 0.9627 4.250 0.5949 0.00969 0.00345 0.0100 0.3399 0.9635 4.500 0.6242 0.00977 0.00353 0.0095 0.3348 0.9642 4.750 0.6526 0.00988 0.00361 0.0092 0.3297 0.9650 5.000 0.6807 0.00998 0.00371 0.0090 0.3250 0.9659 5.250 0.7087 0.01007 0.00383 0.0087 0.3197 0.9668 5.500 0.7359 0.01020 0.00394 0.0087 0.3143 0.9678 5.750 0.7629 0.01030 0.00407 0.0086 0.3093 0.9690 6.000 0.7889 0.01042 0.00420 0.0088 0.3034 0.9703 6.250 0.8134 0.01056 0.00434 0.0092 0.2980 0.9721 6.500 0.8345 0.01066 0.00447 0.0105 0.2924 0.9746 6.750 0.8635 0.01083 0.00465 0.0099 0.2860 0.9752 7.000 0.8928 0.01098 0.00483 0.0093 0.2791 0.9757 7.250 0.9214 0.01117 0.00503 0.0088 0.2718 0.9764 7.500 0.9501 0.01134 0.00524 0.0082 0.2644 0.9771 7.750 0.9779 0.01157 0.00547 0.0078 0.2551 0.9780 8.000 1.0056 0.01178 0.00570 0.0075 0.2459 0.9790 8.250 1.0325 0.01203 0.00597 0.0072 0.2358 0.9802 8.500 1.0583 0.01231 0.00626 0.0071 0.2244 0.9815 8.750 1.0832 0.01263 0.00657 0.0072 0.2132 0.9832 9.000 1.1061 0.01300 0.00693 0.0076 0.1998 0.9852 9.250 1.1315 0.01341 0.00734 0.0075 0.1865 0.9866 9.500 1.1581 0.01389 0.00780 0.0069 0.1709 0.9877 9.750 1.1834 0.01442 0.00830 0.0066 0.1560 0.9890 10.000 1.2071 0.01505 0.00889 0.0064 0.1394 0.9907 10.250 1.2290 0.01576 0.00955 0.0065 0.1231 0.9928 10.500 1.2502 0.01644 0.01022 0.0068 0.1094 0.9950 10.750 1.2726 0.01722 0.01097 0.0066 0.0953 0.9971 11.000 1.2939 0.01805 0.01179 0.0065 0.0824 0.9994 11.250 1.2989 0.01875 0.01248 0.0097 0.0739 1.0000 11.500 1.2975 0.01935 0.01309 0.0143 0.0675 1.0000 11.750 1.2918 0.01998 0.01373 0.0195 0.0622 1.0000 12.000 1.2902 0.02084 0.01460 0.0234 0.0562 1.0000 12.250 1.2929 0.02181 0.01563 0.0261 0.0519 1.0000 12.500 1.2933 0.02314 0.01699 0.0283 0.0465 1.0000 12.750 1.2960 0.02459 0.01850 0.0297 0.0433 1.0000 13.000 1.2967 0.02642 0.02039 0.0307 0.0390 1.0000 13.250 1.2960 0.02862 0.02264 0.0313 0.0355 1.0000 13.500 1.2974 0.03081 0.02491 0.0315 0.0327 1.0000 13.750 1.2960 0.03341 0.02758 0.0314 0.0303 1.0000 14.000 1.2927 0.03632 0.03056 0.0311 0.0281 1.0000 14.250 1.2906 0.03918 0.03351 0.0308 0.0262 1.0000 14.500 1.2853 0.04246 0.03687 0.0303 0.0241 1.0000 14.750 1.2776 0.04607 0.04055 0.0296 0.0225 1.0000 15.000 1.2711 0.04960 0.04417 0.0288 0.0209 1.0000 15.250 1.2653 0.05310 0.04777 0.0280 0.0201 1.0000 15.500 1.2558 0.05710 0.05185 0.0270 0.0183 1.0000 15.750 1.2478 0.06107 0.05591 0.0259 0.0175 1.0000 16.000 1.2394 0.06524 0.06016 0.0246 0.0165 1.0000 16.250 1.2326 0.06928 0.06429 0.0233 0.0154 1.0000 16.500 1.2252 0.07348 0.06859 0.0219 0.0148 1.0000 16.750 1.2159 0.07806 0.07323 0.0202 0.0135 1.0000 17.000 1.2078 0.08255 0.07781 0.0186 0.0131 1.0000 17.250 1.1997 0.08712 0.08246 0.0168 0.0124 1.0000 17.500 1.1934 0.09154 0.08698 0.0151 0.0119 1.0000 17.750 1.1865 0.09614 0.09168 0.0132 0.0117 1.0000 18.000 1.1787 0.10086 0.09646 0.0112 0.0103 1.0000 18.250 1.1719 0.10553 0.10123 0.0092 0.0100 1.0000 18.500 1.1630 0.11067 0.10643 0.0069 0.0095 1.0000 18.750 1.1564 0.11545 0.11129 0.0046 0.0082 1.0000