XFOIL Version 6.96 Calculated polar for: GOE 229 (MVA H.39) 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 ------ -------- --------- --------- -------- -------- -------- -18.750 -0.6328 0.11346 0.11105 -0.0722 1.0000 0.0070 -18.500 -0.6606 0.10483 0.10228 -0.0768 1.0000 0.0070 -18.250 -0.6810 0.09770 0.09504 -0.0807 1.0000 0.0070 -18.000 -0.6963 0.09168 0.08892 -0.0840 1.0000 0.0071 -17.750 -0.7087 0.08625 0.08340 -0.0869 1.0000 0.0071 -17.500 -0.7171 0.08114 0.07819 -0.0901 0.9974 0.0072 -17.250 -0.7208 0.07617 0.07313 -0.0941 0.9909 0.0072 -17.000 -0.7214 0.07169 0.06856 -0.0978 0.9829 0.0073 -16.750 -0.7210 0.06764 0.06441 -0.1010 0.9724 0.0074 -16.500 -0.7212 0.06388 0.06055 -0.1036 0.9595 0.0074 -16.250 -0.7228 0.06045 0.05702 -0.1054 0.9451 0.0075 -16.000 -0.7226 0.05747 0.05393 -0.1067 0.9316 0.0076 -15.750 -0.7222 0.05455 0.05088 -0.1081 0.9194 0.0076 -15.500 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0.00500 -0.1566 0.5706 0.0270 -6.000 0.0760 0.01144 0.00483 -0.1568 0.5530 0.0276 -5.750 0.1035 0.01143 0.00470 -0.1569 0.5346 0.0280 -5.500 0.1313 0.01136 0.00454 -0.1571 0.5192 0.0285 -5.250 0.1588 0.01124 0.00428 -0.1574 0.5019 0.0294 -5.000 0.1867 0.01115 0.00409 -0.1576 0.4879 0.0305 -4.750 0.2145 0.01110 0.00396 -0.1578 0.4728 0.0316 -4.500 0.2417 0.01112 0.00386 -0.1579 0.4511 0.0324 -4.250 0.2673 0.01127 0.00381 -0.1577 0.4161 0.0332 -4.000 0.2734 0.01283 0.00444 -0.1543 0.2057 0.0338 -3.750 0.2989 0.01300 0.00446 -0.1541 0.1767 0.0346 -3.250 0.3494 0.01339 0.00458 -0.1536 0.0999 0.0367 -3.000 0.3771 0.01339 0.00455 -0.1537 0.0976 0.0406 -2.750 0.4047 0.01341 0.00454 -0.1538 0.0951 0.0453 -2.500 0.4326 0.01322 0.00447 -0.1543 0.0916 0.0993 -2.250 0.4604 0.01315 0.00444 -0.1545 0.0899 0.1244 -2.000 0.4894 0.01251 0.00423 -0.1557 0.0874 0.2732 -1.750 0.5163 0.01253 0.00430 -0.1558 0.0817 0.3098 -1.250 0.5685 0.01282 0.00457 -0.1555 0.0535 0.3415 -1.000 0.5951 0.01294 0.00470 -0.1554 0.0517 0.3526 -0.750 0.6215 0.01308 0.00484 -0.1553 0.0504 0.3646 -0.500 0.6476 0.01322 0.00498 -0.1552 0.0493 0.3718 -0.250 0.6734 0.01339 0.00513 -0.1549 0.0483 0.3764 0.000 0.6989 0.01357 0.00529 -0.1547 0.0475 0.3800 0.250 0.7243 0.01373 0.00546 -0.1544 0.0468 0.3857 0.500 0.7492 0.01392 0.00564 -0.1540 0.0461 0.3928 0.750 0.7737 0.01412 0.00583 -0.1536 0.0454 0.3967 1.000 0.7978 0.01431 0.00602 -0.1531 0.0448 0.3995 1.250 0.8200 0.01452 0.00623 -0.1522 0.0442 0.4022 1.500 0.8410 0.01474 0.00646 -0.1511 0.0436 0.4052 1.750 0.8627 0.01496 0.00668 -0.1502 0.0432 0.4086 2.000 0.8851 0.01522 0.00693 -0.1494 0.0427 0.4119 2.250 0.9076 0.01550 0.00722 -0.1487 0.0422 0.4152 2.500 0.9298 0.01579 0.00752 -0.1480 0.0418 0.4187 2.750 0.9517 0.01611 0.00784 -0.1473 0.0414 0.4214 3.000 0.9731 0.01644 0.00819 -0.1465 0.0410 0.4243 3.250 0.9941 0.01680 0.00855 -0.1457 0.0407 0.4273 3.500 1.0147 0.01718 0.00894 -0.1448 0.0404 0.4297 3.750 1.0347 0.01759 0.00936 -0.1439 0.0401 0.4318 4.000 1.0544 0.01803 0.00982 -0.1429 0.0399 0.4348 4.250 1.0732 0.01852 0.01035 -0.1419 0.0396 0.4377 4.500 1.0921 0.01902 0.01087 -0.1409 0.0394 0.4406 4.750 1.1106 0.01955 0.01141 -0.1399 0.0393 0.4435 5.000 1.1288 0.02011 0.01200 -0.1389 0.0392 0.4464 5.500 1.1637 0.02135 0.01330 -0.1369 0.0389 0.4527 5.750 1.1805 0.02204 0.01402 -0.1358 0.0388 0.4563 6.000 1.1978 0.02271 0.01472 -0.1349 0.0384 0.4598 6.250 1.2155 0.02336 0.01539 -0.1340 0.0377 0.4631 6.500 1.2329 0.02405 0.01609 -0.1332 0.0371 0.4660 6.750 1.2495 0.02480 0.01687 -0.1323 0.0367 0.4695 7.000 1.2665 0.02554 0.01764 -0.1315 0.0362 0.4734 7.250 1.2828 0.02635 0.01846 -0.1306 0.0358 0.4774 7.500 1.2973 0.02729 0.01944 -0.1296 0.0354 0.4811 8.000 1.3287 0.02905 0.02128 -0.1280 0.0341 0.4899 8.250 1.3445 0.02994 0.02221 -0.1273 0.0332 0.4952 8.500 1.3600 0.03088 0.02316 -0.1266 0.0323 0.5000 8.750 1.3753 0.03182 0.02413 -0.1258 0.0309 0.5047 9.000 1.3894 0.03288 0.02522 -0.1251 0.0276 0.5102 9.250 1.3975 0.03445 0.02673 -0.1239 0.0124 0.5155 9.750 1.4146 0.03769 0.03012 -0.1217 0.0103 0.5270 10.000 1.4237 0.03929 0.03178 -0.1207 0.0097 0.5340 10.250 1.4319 0.04102 0.03359 -0.1198 0.0092 0.5419 10.500 1.4391 0.04289 0.03554 -0.1189 0.0087 0.5520 10.750 1.4457 0.04485 0.03758 -0.1180 0.0082 0.5628 11.000 1.4535 0.04671 0.03952 -0.1172 0.0079 0.5754 11.250 1.4606 0.04867 0.04157 -0.1164 0.0075 0.5896 11.500 1.4677 0.05066 0.04365 -0.1157 0.0072 0.6041 11.750 1.4736 0.05282 0.04588 -0.1151 0.0069 0.6182 12.000 1.4795 0.05498 0.04812 -0.1144 0.0066 0.6315 12.250 1.4847 0.05727 0.05048 -0.1138 0.0064 0.6441 12.500 1.4886 0.05970 0.05298 -0.1132 0.0061 0.6557 12.750 1.4938 0.06202 0.05538 -0.1127 0.0060 0.6675 13.000 1.4977 0.06453 0.05797 -0.1122 0.0059 0.6795 13.250 1.5014 0.06709 0.06063 -0.1118 0.0057 0.6922 13.500 1.5046 0.06973 0.06336 -0.1114 0.0055 0.7058 13.750 1.5068 0.07253 0.06626 -0.1110 0.0054 0.7243 14.000 1.5106 0.07509 0.06915 -0.1109 0.0052 0.8404 14.250 1.5095 0.07771 0.07200 -0.1100 0.0051 1.0000 14.500 1.5104 0.08070 0.07505 -0.1098 0.0049 1.0000 14.750 1.5110 0.08375 0.07815 -0.1095 0.0048 1.0000 15.000 1.5100 0.08705 0.08151 -0.1094 0.0046 1.0000 15.250 1.5086 0.09036 0.08490 -0.1093 0.0045 1.0000 15.500 1.5065 0.09383 0.08843 -0.1092 0.0044 1.0000 15.750 1.5063 0.09704 0.09171 -0.1093 0.0043 1.0000 16.000 1.5043 0.10057 0.09531 -0.1094 0.0043 1.0000 16.250 1.5033 0.10395 0.09875 -0.1095 0.0042 1.0000 16.500 1.5005 0.10762 0.10250 -0.1098 0.0041 1.0000 16.750 1.4983 0.11117 0.10612 -0.1101 0.0040 1.0000 17.000 1.4952 0.11492 0.10994 -0.1106 0.0040 1.0000 17.250 1.4921 0.11869 0.11379 -0.1111 0.0039 1.0000 17.500 1.4892 0.12247 0.11764 -0.1118 0.0038 1.0000 17.750 1.4852 0.12646 0.12170 -0.1126 0.0038 1.0000 18.000 1.4826 0.13025 0.12555 -0.1134 0.0037 1.0000 18.250 1.4780 0.13438 0.12976 -0.1145 0.0036 1.0000 18.500 1.4745 0.13835 0.13381 -0.1155 0.0036 1.0000 18.750 1.4704 0.14246 0.13799 -0.1168 0.0035 1.0000 19.000 1.4660 0.14670 0.14230 -0.1182 0.0035 1.0000 19.250 1.4627 0.15076 0.14643 -0.1197 0.0034 1.0000