XFOIL Version 6.96 Calculated polar for: EPPLER 331 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4590 0.08184 0.07947 -0.0165 0.7236 0.0046 -8.750 -0.4697 0.07691 0.07450 -0.0205 0.7055 0.0046 -8.500 -0.4813 0.07290 0.07041 -0.0221 0.6873 0.0046 -8.250 -0.4965 0.06921 0.06665 -0.0213 0.6741 0.0046 -6.750 -0.5072 0.03167 0.02840 -0.0086 0.5939 0.0028 -6.250 -0.5567 0.01953 0.01419 0.0065 0.6018 0.0028 -6.000 -0.5351 0.01796 0.01231 0.0078 0.5901 0.0028 -5.750 -0.5144 0.01589 0.00984 0.0092 0.5787 0.0032 -5.250 -0.4647 0.01467 0.00834 0.0105 0.5549 0.0034 -5.000 -0.4395 0.01413 0.00768 0.0110 0.5450 0.0036 -4.750 -0.4143 0.01353 0.00695 0.0117 0.5342 0.0037 -4.500 -0.3890 0.01301 0.00630 0.0123 0.5235 0.0038 -4.250 -0.3636 0.01255 0.00574 0.0129 0.5133 0.0040 -3.750 -0.3133 0.01169 0.00470 0.0141 0.4951 0.0042 -3.500 -0.2878 0.01139 0.00431 0.0147 0.4857 0.0043 -3.250 -0.2626 0.01106 0.00391 0.0153 0.4765 0.0044 -3.000 -0.2369 0.01081 0.00361 0.0159 0.4688 0.0046 -2.750 -0.2117 0.01050 0.00324 0.0165 0.4607 0.0049 -2.500 -0.1861 0.01027 0.00296 0.0170 0.4531 0.0052 -2.250 -0.1603 0.01008 0.00272 0.0175 0.4447 0.0054 -2.000 -0.1344 0.00988 0.00247 0.0180 0.4378 0.0056 -1.750 -0.1083 0.00971 0.00226 0.0185 0.4308 0.0059 -1.500 -0.0820 0.00958 0.00208 0.0189 0.4240 0.0064 -1.250 -0.0556 0.00945 0.00191 0.0193 0.4167 0.0071 -1.000 -0.0296 0.00932 0.00176 0.0197 0.4100 0.0126 -0.750 -0.0035 0.00915 0.00166 0.0201 0.4043 0.0310 -0.500 0.0220 0.00899 0.00157 0.0206 0.3977 0.0652 -0.250 0.0461 0.00868 0.00150 0.0213 0.3918 0.1462 0.000 0.0304 0.00609 0.00117 0.0297 0.3888 0.7873 0.250 0.0510 0.00606 0.00142 0.0318 0.3835 0.8929 0.500 0.0775 0.00618 0.00151 0.0324 0.3782 0.9061 0.750 0.1039 0.00632 0.00162 0.0330 0.3726 0.9174 1.000 0.1295 0.00647 0.00172 0.0337 0.3670 0.9257 1.250 0.1572 0.00658 0.00180 0.0339 0.3624 0.9305 1.500 0.1858 0.00669 0.00187 0.0339 0.3573 0.9335 1.750 0.2135 0.00675 0.00187 0.0339 0.3516 0.9346 2.000 0.2413 0.00679 0.00188 0.0339 0.3474 0.9355 2.250 0.2691 0.00684 0.00189 0.0339 0.3427 0.9367 2.500 0.2965 0.00690 0.00190 0.0340 0.3374 0.9378 2.750 0.3239 0.00696 0.00193 0.0340 0.3329 0.9388 3.000 0.3514 0.00700 0.00195 0.0340 0.3287 0.9397 3.250 0.3786 0.00706 0.00198 0.0341 0.3235 0.9407 3.500 0.4057 0.00714 0.00202 0.0342 0.3186 0.9416 3.750 0.4330 0.00719 0.00206 0.0342 0.3143 0.9425 4.000 0.4610 0.00726 0.00211 0.0341 0.3087 0.9434 4.250 0.4887 0.00735 0.00218 0.0340 0.3038 0.9442 4.500 0.5166 0.00742 0.00224 0.0339 0.2987 0.9449 4.750 0.5441 0.00752 0.00233 0.0339 0.2928 0.9457 5.000 0.5716 0.00762 0.00242 0.0338 0.2877 0.9465 5.250 0.5991 0.00771 0.00250 0.0337 0.2822 0.9474 5.500 0.6261 0.00783 0.00261 0.0338 0.2756 0.9483 5.750 0.6534 0.00793 0.00272 0.0337 0.2700 0.9493 6.000 0.6802 0.00806 0.00283 0.0338 0.2631 0.9503 6.250 0.7069 0.00818 0.00295 0.0338 0.2563 0.9514 6.500 0.7331 0.00834 0.00309 0.0339 0.2482 0.9527 6.750 0.7594 0.00847 0.00323 0.0340 0.2415 0.9541 7.000 0.7848 0.00866 0.00339 0.0343 0.2314 0.9553 7.250 0.8106 0.00882 0.00355 0.0344 0.2229 0.9565 7.500 0.8362 0.00902 0.00373 0.0346 0.2140 0.9576 7.750 0.8621 0.00925 0.00395 0.0347 0.2031 0.9587 8.000 0.8878 0.00950 0.00417 0.0347 0.1913 0.9598 8.250 0.9131 0.00977 0.00442 0.0349 0.1791 0.9610 8.500 0.9377 0.01008 0.00470 0.0351 0.1665 0.9624 8.750 0.9611 0.01046 0.00503 0.0355 0.1509 0.9641 9.000 0.9843 0.01084 0.00537 0.0359 0.1373 0.9659 9.250 1.0065 0.01124 0.00573 0.0365 0.1236 0.9680 9.500 1.0273 0.01168 0.00613 0.0374 0.1100 0.9704 9.750 1.0500 0.01220 0.00658 0.0376 0.0948 0.9723 10.000 1.0740 0.01272 0.00707 0.0376 0.0822 0.9739 10.250 1.0968 0.01331 0.00761 0.0378 0.0688 0.9758 10.500 1.1184 0.01394 0.00820 0.0380 0.0565 0.9780 10.750 1.1403 0.01448 0.00873 0.0383 0.0495 0.9804 11.000 1.1569 0.01538 0.00953 0.0392 0.0348 0.9837 11.250 1.1804 0.01617 0.01030 0.0386 0.0264 0.9850 11.500 1.2030 0.01703 0.01114 0.0381 0.0197 0.9863 11.750 1.2262 0.01772 0.01187 0.0377 0.0169 0.9879 12.000 1.2455 0.01860 0.01276 0.0376 0.0130 0.9905 12.250 1.2619 0.01943 0.01364 0.0381 0.0110 0.9939 12.500 1.2813 0.02029 0.01456 0.0377 0.0101 0.9972 13.000 1.2932 0.02259 0.01697 0.0404 0.0077 1.0000 13.250 1.2907 0.02412 0.01856 0.0424 0.0065 1.0000 13.500 1.2937 0.02568 0.02020 0.0434 0.0068 1.0000 13.750 1.2928 0.02787 0.02245 0.0438 0.0057 1.0000 14.000 1.2925 0.03022 0.02488 0.0439 0.0049 1.0000 14.250 1.2910 0.03286 0.02759 0.0436 0.0041 1.0000 14.500 1.2881 0.03576 0.03057 0.0432 0.0036 1.0000 14.750 1.2866 0.03856 0.03347 0.0427 0.0037 1.0000 15.000 1.2825 0.04172 0.03671 0.0421 0.0034 1.0000 15.250 1.2768 0.04508 0.04016 0.0414 0.0031 1.0000 15.500 1.2714 0.04846 0.04363 0.0406 0.0031 1.0000 15.750 1.2630 0.05223 0.04748 0.0396 0.0029 1.0000 16.000 1.2503 0.05658 0.05191 0.0384 0.0021 1.0000 16.250 1.2423 0.06051 0.05592 0.0373 0.0021 1.0000 16.500 1.2332 0.06469 0.06018 0.0359 0.0018 1.0000 16.750 1.2228 0.06914 0.06472 0.0344 0.0016 1.0000 17.000 1.2109 0.07390 0.06956 0.0327 0.0011 1.0000 17.250 1.2102 0.07714 0.07290 0.0317 0.0020 1.0000 17.500 1.1978 0.08207 0.07790 0.0299 0.0014 1.0000 17.750 1.1891 0.08659 0.08251 0.0282 0.0014 1.0000