XFOIL Version 6.96 Calculated polar for: EPPLER 327 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.4492 0.12250 0.11749 -0.0143 1.0000 0.0488 -11.000 -0.4532 0.11825 0.11330 -0.0178 1.0000 0.0491 -10.750 -0.4561 0.11381 0.10891 -0.0211 1.0000 0.0492 -10.500 -0.4603 0.10898 0.10412 -0.0247 1.0000 0.0493 -10.250 -0.4611 0.10396 0.09917 -0.0270 1.0000 0.0495 -10.000 -0.4506 0.10045 0.09569 -0.0252 1.0000 0.0500 -9.500 -0.3684 0.07992 0.07549 -0.0309 1.0000 0.0266 -9.000 -0.4793 0.07676 0.07193 -0.0348 1.0000 0.0267 -8.750 -0.4844 0.07379 0.06899 -0.0340 1.0000 0.0261 -8.500 -0.4948 0.07083 0.06602 -0.0326 1.0000 0.0257 -8.250 -0.5073 0.06789 0.06305 -0.0302 1.0000 0.0251 -7.750 -0.5366 0.05884 0.05356 -0.0240 1.0000 0.0218 -7.500 -0.5380 0.05618 0.05083 -0.0213 1.0000 0.0216 -7.250 -0.5386 0.05357 0.04811 -0.0184 1.0000 0.0213 -7.000 -0.5392 0.05085 0.04526 -0.0152 1.0000 0.0210 -6.750 -0.5391 0.04815 0.04240 -0.0118 1.0000 0.0207 -6.500 -0.5261 0.04472 0.03869 -0.0109 0.9881 0.0202 -6.250 -0.5028 0.04060 0.03413 -0.0114 0.9611 0.0196 -6.000 -0.4756 0.03665 0.02963 -0.0119 0.9331 0.0192 -5.750 -0.4430 0.03315 0.02556 -0.0130 0.9080 0.0191 -5.500 -0.4071 0.03016 0.02202 -0.0144 0.8831 0.0192 -5.250 -0.3723 0.02781 0.01920 -0.0154 0.8566 0.0194 -5.000 -0.3395 0.02603 0.01703 -0.0158 0.8306 0.0203 -4.750 -0.3086 0.02450 0.01507 -0.0157 0.8061 0.0223 -4.500 -0.2815 0.02350 0.01395 -0.0155 0.7833 0.0243 -4.250 -0.2533 0.02232 0.01257 -0.0151 0.7620 0.0255 -4.000 -0.2267 0.02127 0.01129 -0.0143 0.7429 0.0269 -3.750 -0.2038 0.02038 0.01037 -0.0132 0.7251 0.0294 -3.500 -0.1810 0.01974 0.00958 -0.0121 0.7084 0.0336 -3.250 -0.1589 0.01912 0.00886 -0.0108 0.6926 0.0395 -3.000 -0.1371 0.01849 0.00818 -0.0095 0.6778 0.0502 -2.750 -0.1156 0.01775 0.00756 -0.0081 0.6641 0.0824 -2.500 -0.0828 0.01594 0.00891 -0.0064 0.6513 0.7762 -2.250 -0.0749 0.01675 0.00949 -0.0008 0.6399 0.8354 -2.000 0.0226 0.01906 0.01131 -0.0095 0.6220 0.8906 -1.750 0.0769 0.01954 0.01143 -0.0134 0.6079 0.9107 -1.500 0.1029 0.01949 0.01118 -0.0131 0.5959 0.9170 -1.250 0.1347 0.01937 0.01085 -0.0141 0.5844 0.9200 -1.000 0.1630 0.01929 0.01056 -0.0143 0.5740 0.9238 -0.750 0.1860 0.01925 0.01036 -0.0136 0.5639 0.9283 -0.500 0.2113 0.01918 0.01015 -0.0133 0.5541 0.9318 -0.250 0.2417 0.01910 0.00989 -0.0140 0.5450 0.9342 0.000 0.2703 0.01904 0.00972 -0.0144 0.5352 0.9370 0.250 0.2963 0.01902 0.00954 -0.0143 0.5272 0.9401 0.500 0.3188 0.01902 0.00947 -0.0135 0.5184 0.9435 0.750 0.3438 0.01901 0.00934 -0.0132 0.5112 0.9462 1.000 0.3734 0.01897 0.00924 -0.0138 0.5025 0.9482 1.250 0.4013 0.01896 0.00912 -0.0141 0.4956 0.9503 1.500 0.4281 0.01897 0.00910 -0.0142 0.4876 0.9527 1.750 0.4531 0.01901 0.00904 -0.0139 0.4814 0.9551 2.000 0.4762 0.01907 0.00911 -0.0133 0.4740 0.9577 2.250 0.5004 0.01913 0.00910 -0.0129 0.4676 0.9600 2.500 0.5285 0.01917 0.00912 -0.0133 0.4610 0.9615 2.750 0.5562 0.01922 0.00917 -0.0136 0.4541 0.9633 3.000 0.5832 0.01930 0.00919 -0.0138 0.4484 0.9652 3.250 0.6085 0.01940 0.00933 -0.0136 0.4416 0.9672 3.500 0.6329 0.01950 0.00940 -0.0133 0.4359 0.9691 3.750 0.6564 0.01965 0.00960 -0.0128 0.4300 0.9714 4.000 0.6814 0.01978 0.00976 -0.0126 0.4238 0.9732 4.250 0.7083 0.01988 0.00982 -0.0128 0.4186 0.9745 4.500 0.7341 0.02005 0.01011 -0.0128 0.4119 0.9760 4.750 0.7605 0.02019 0.01028 -0.0129 0.4061 0.9779 5.000 0.7862 0.02037 0.01049 -0.0129 0.4007 0.9799 5.250 0.8100 0.02058 0.01083 -0.0126 0.3942 0.9818 5.500 0.8335 0.02077 0.01103 -0.0121 0.3891 0.9835 5.750 0.8582 0.02100 0.01136 -0.0120 0.3829 0.9850 6.000 0.8845 0.02121 0.01168 -0.0121 0.3766 0.9867 6.250 0.9112 0.02140 0.01187 -0.0123 0.3713 0.9886 6.500 0.9357 0.02169 0.01236 -0.0123 0.3642 0.9907 6.750 0.9603 0.02190 0.01263 -0.0121 0.3583 0.9925 7.000 0.9835 0.02222 0.01309 -0.0118 0.3516 0.9944 7.250 1.0084 0.02245 0.01343 -0.0117 0.3447 0.9962 7.500 1.0327 0.02274 0.01382 -0.0116 0.3380 0.9981 7.750 1.0560 0.02303 0.01428 -0.0114 0.3303 1.0000 8.000 1.0724 0.02332 0.01464 -0.0097 0.3243 1.0000 8.250 1.0863 0.02369 0.01519 -0.0076 0.3167 1.0000 8.500 1.1015 0.02395 0.01549 -0.0057 0.3104 1.0000 8.750 1.1128 0.02437 0.01612 -0.0032 0.3023 1.0000 9.000 1.1258 0.02463 0.01642 -0.0009 0.2957 1.0000 9.250 1.1342 0.02507 0.01706 0.0020 0.2873 1.0000 9.500 1.1436 0.02538 0.01743 0.0048 0.2803 1.0000 9.750 1.1487 0.02582 0.01805 0.0082 0.2717 1.0000 10.000 1.1533 0.02619 0.01849 0.0118 0.2645 1.0000 10.250 1.1544 0.02662 0.01904 0.0158 0.2563 1.0000 10.500 1.1545 0.02706 0.01957 0.0200 0.2487 1.0000 10.750 1.1533 0.02754 0.02011 0.0242 0.2407 1.0000 11.000 1.1520 0.02816 0.02083 0.0281 0.2323 1.0000 11.250 1.1495 0.02878 0.02145 0.0321 0.2244 1.0000 11.500 1.1473 0.02974 0.02254 0.0354 0.2151 1.0000 11.750 1.1459 0.03087 0.02372 0.0380 0.2061 1.0000 12.000 1.1433 0.03228 0.02516 0.0400 0.1970 1.0000 12.250 1.1398 0.03409 0.02709 0.0415 0.1876 1.0000 12.500 1.1353 0.03620 0.02924 0.0424 0.1789 1.0000 12.750 1.1291 0.03869 0.03178 0.0429 0.1702 1.0000 13.000 1.1220 0.04158 0.03476 0.0429 0.1615 1.0000 13.250 1.1145 0.04462 0.03782 0.0427 0.1541 1.0000 13.500 1.1058 0.04804 0.04134 0.0422 0.1462 1.0000 13.750 1.0966 0.05163 0.04496 0.0414 0.1391 1.0000 14.000 1.0868 0.05544 0.04885 0.0405 0.1321 1.0000 14.250 1.0779 0.05922 0.05266 0.0395 0.1258 1.0000 14.500 1.0675 0.06333 0.05684 0.0382 0.1193 1.0000 14.750 1.0594 0.06723 0.06076 0.0370 0.1135 1.0000 15.000 1.0508 0.07143 0.06506 0.0356 0.1076 1.0000 15.250 1.0440 0.07537 0.06898 0.0342 0.1022 1.0000 15.500 1.0362 0.07979 0.07352 0.0325 0.0967 1.0000 15.750 1.0306 0.08370 0.07740 0.0310 0.0917 1.0000 16.000 1.0236 0.08821 0.08205 0.0292 0.0867 1.0000 16.250 1.0177 0.09251 0.08639 0.0274 0.0822 1.0000