XFOIL Version 6.96 Calculated polar for: EPPLER 636 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 ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4244 0.08849 0.08554 -0.0126 0.7101 0.0128 -9.000 -0.4467 0.07997 0.07702 -0.0179 0.7002 0.0117 -8.750 -0.4581 0.07527 0.07228 -0.0216 0.6845 0.0118 -7.750 -0.5014 0.05702 0.05355 -0.0207 0.6387 0.0110 -7.500 -0.5013 0.05345 0.04983 -0.0195 0.6275 0.0108 -7.250 -0.5009 0.04886 0.04502 -0.0178 0.6178 0.0108 -7.000 -0.4967 0.04480 0.04072 -0.0159 0.6075 0.0108 -6.750 -0.4943 0.03901 0.03457 -0.0130 0.5991 0.0109 -6.500 -0.4903 0.03332 0.02843 -0.0096 0.5913 0.0110 -6.250 -0.4813 0.02921 0.02382 -0.0066 0.5822 0.0111 -6.000 -0.4674 0.02643 0.02060 -0.0042 0.5723 0.0112 -5.750 -0.4527 0.02374 0.01753 -0.0021 0.5633 0.0115 -5.500 -0.4322 0.02239 0.01597 -0.0009 0.5529 0.0117 -5.250 -0.4100 0.02129 0.01468 0.0001 0.5428 0.0120 -5.000 -0.3870 0.02030 0.01348 0.0010 0.5327 0.0122 -4.750 -0.3635 0.01890 0.01182 0.0020 0.5231 0.0123 -4.500 -0.3389 0.01778 0.01046 0.0028 0.5145 0.0124 -4.250 -0.3136 0.01686 0.00936 0.0035 0.5058 0.0126 -4.000 -0.2878 0.01607 0.00842 0.0041 0.4975 0.0129 -3.500 -0.2360 0.01475 0.00684 0.0052 0.4803 0.0135 -3.250 -0.2102 0.01423 0.00620 0.0058 0.4727 0.0138 -3.000 -0.1845 0.01373 0.00562 0.0064 0.4655 0.0141 -2.500 -0.1336 0.01296 0.00470 0.0076 0.4512 0.0147 -2.250 -0.1077 0.01275 0.00442 0.0081 0.4441 0.0151 -2.000 -0.0838 0.01223 0.00386 0.0090 0.4380 0.0158 -1.750 -0.0589 0.01191 0.00350 0.0097 0.4320 0.0164 -1.500 -0.0336 0.01167 0.00321 0.0104 0.4262 0.0168 -1.250 -0.0079 0.01146 0.00297 0.0109 0.4200 0.0174 -1.000 0.0178 0.01131 0.00275 0.0115 0.4140 0.0181 -0.750 0.0440 0.01117 0.00258 0.0119 0.4089 0.0190 -0.500 0.0703 0.01107 0.00242 0.0123 0.4036 0.0198 -0.250 0.0964 0.01098 0.00228 0.0128 0.3985 0.0215 0.000 0.1228 0.01087 0.00218 0.0132 0.3936 0.0261 0.500 0.1616 0.00950 0.00197 0.0162 0.3847 0.4070 0.750 0.2005 0.00797 0.00222 0.0141 0.3802 0.9143 1.000 0.2502 0.00838 0.00257 0.0100 0.3744 0.9410 1.250 0.2920 0.00890 0.00299 0.0076 0.3692 0.9584 1.500 0.3342 0.00905 0.00308 0.0047 0.3648 0.9607 1.750 0.3660 0.00912 0.00309 0.0038 0.3606 0.9621 2.000 0.3969 0.00920 0.00311 0.0031 0.3565 0.9638 2.250 0.4265 0.00928 0.00314 0.0027 0.3528 0.9658 2.500 0.4544 0.00935 0.00318 0.0027 0.3487 0.9684 2.750 0.4784 0.00944 0.00325 0.0035 0.3451 0.9716 3.000 0.5105 0.00952 0.00328 0.0025 0.3414 0.9725 3.250 0.5422 0.00960 0.00333 0.0016 0.3379 0.9735 3.500 0.5734 0.00966 0.00338 0.0008 0.3340 0.9747 3.750 0.6040 0.00974 0.00344 0.0001 0.3300 0.9761 4.000 0.6338 0.00985 0.00352 -0.0005 0.3266 0.9777 4.250 0.6628 0.00994 0.00361 -0.0008 0.3234 0.9795 4.500 0.6907 0.01003 0.00371 -0.0009 0.3197 0.9814 4.750 0.7165 0.01015 0.00384 -0.0006 0.3161 0.9836 5.000 0.7479 0.01025 0.00392 -0.0015 0.3125 0.9845 5.250 0.7788 0.01035 0.00402 -0.0024 0.3092 0.9854 5.500 0.8094 0.01042 0.00414 -0.0031 0.3053 0.9864 5.750 0.8399 0.01053 0.00426 -0.0039 0.3014 0.9876 6.000 0.8696 0.01066 0.00438 -0.0045 0.2976 0.9890 6.250 0.8988 0.01078 0.00453 -0.0050 0.2937 0.9903 6.500 0.9275 0.01089 0.00469 -0.0054 0.2894 0.9916 6.750 0.9559 0.01104 0.00485 -0.0058 0.2839 0.9930 7.000 0.9844 0.01119 0.00502 -0.0062 0.2785 0.9943 7.250 1.0147 0.01131 0.00519 -0.0070 0.2732 0.9952 7.500 1.0438 0.01149 0.00537 -0.0076 0.2680 0.9962 7.750 1.0733 0.01162 0.00556 -0.0083 0.2629 0.9972 8.000 1.1026 0.01180 0.00576 -0.0090 0.2564 0.9984 8.250 1.1319 0.01199 0.00600 -0.0096 0.2495 0.9994 8.500 1.1582 0.01222 0.00625 -0.0097 0.2421 1.0000 8.750 1.1799 0.01248 0.00652 -0.0089 0.2316 1.0000 9.000 1.2008 0.01280 0.00684 -0.0079 0.2202 1.0000 9.250 1.2205 0.01320 0.00721 -0.0068 0.2046 1.0000 9.500 1.2387 0.01372 0.00766 -0.0055 0.1863 1.0000 9.750 1.2551 0.01436 0.00821 -0.0041 0.1645 1.0000 10.000 1.2691 0.01515 0.00890 -0.0023 0.1421 1.0000 10.250 1.2824 0.01594 0.00962 -0.0004 0.1233 1.0000 10.500 1.2954 0.01669 0.01034 0.0016 0.1094 1.0000 10.750 1.3053 0.01759 0.01118 0.0039 0.0943 1.0000 11.000 1.3136 0.01849 0.01204 0.0064 0.0804 1.0000 11.250 1.3191 0.01948 0.01298 0.0093 0.0673 1.0000 11.500 1.3227 0.02046 0.01395 0.0124 0.0580 1.0000 11.750 1.3168 0.02158 0.01505 0.0170 0.0485 1.0000 12.000 1.3109 0.02252 0.01603 0.0213 0.0445 1.0000 12.250 1.3011 0.02415 0.01769 0.0247 0.0388 1.0000 12.500 1.2940 0.02628 0.01988 0.0264 0.0335 1.0000 12.750 1.2884 0.02880 0.02245 0.0272 0.0291 1.0000 13.000 1.2777 0.03217 0.02586 0.0273 0.0232 1.0000 13.250 1.2713 0.03531 0.02907 0.0272 0.0201 1.0000 13.500 1.2591 0.03919 0.03299 0.0268 0.0156 1.0000 13.750 1.2466 0.04320 0.03707 0.0263 0.0121 1.0000 14.000 1.2354 0.04711 0.04105 0.0257 0.0102 1.0000 14.250 1.2297 0.05044 0.04447 0.0253 0.0100 1.0000 14.500 1.2145 0.05494 0.04903 0.0244 0.0081 1.0000 14.750 1.2043 0.05892 0.05309 0.0236 0.0074 1.0000 15.000 1.1968 0.06273 0.05699 0.0228 0.0071 1.0000 15.250 1.1882 0.06681 0.06115 0.0218 0.0067 1.0000 15.500 1.1831 0.07049 0.06491 0.0208 0.0066 1.0000 15.750 1.1743 0.07474 0.06924 0.0196 0.0061 1.0000 16.000 1.1676 0.07880 0.07338 0.0185 0.0059 1.0000 16.250 1.1613 0.08285 0.07752 0.0173 0.0057 1.0000 16.500 1.1555 0.08690 0.08165 0.0160 0.0055 1.0000 16.750 1.1504 0.09089 0.08573 0.0148 0.0055 1.0000 17.000 1.1430 0.09527 0.09021 0.0134 0.0052 1.0000 17.250 1.1377 0.09939 0.09442 0.0120 0.0051 1.0000