XFOIL Version 6.96 Calculated polar for: GOE 336 (MVA H.44) 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.3244 0.10485 0.10328 -0.0241 1.0000 0.0155 -9.250 -0.3218 0.10115 0.09960 -0.0261 1.0000 0.0155 -9.000 -0.3185 0.09761 0.09606 -0.0279 1.0000 0.0156 -8.750 -0.3161 0.09405 0.09253 -0.0295 1.0000 0.0156 -8.500 -0.3128 0.09034 0.08883 -0.0297 0.9986 0.0159 -8.250 -0.2950 0.08737 0.08586 -0.0330 0.9837 0.0162 -8.000 -0.2795 0.08432 0.08278 -0.0365 0.9516 0.0165 -7.750 -0.2752 0.08182 0.08014 -0.0374 0.8982 0.0169 -7.500 -0.2694 0.07920 0.07731 -0.0392 0.8448 0.0175 -7.250 -0.2564 0.07425 0.07214 -0.0468 0.7977 0.0194 -7.000 -0.2420 0.06978 0.06750 -0.0516 0.7699 0.0195 -6.750 -0.2258 0.06527 0.06286 -0.0557 0.7522 0.0195 -6.500 -0.2160 0.05949 0.05697 -0.0594 0.7397 0.0200 -6.250 -0.1982 0.05757 0.05497 -0.0603 0.7279 0.0203 -5.000 -0.0874 0.03702 0.03372 -0.0722 0.6883 0.0251 -4.750 -0.0654 0.03572 0.03232 -0.0724 0.6802 0.0255 -4.500 -0.0420 0.03432 0.03085 -0.0726 0.6718 0.0260 -4.250 -0.0182 0.03273 0.02914 -0.0729 0.6635 0.0268 -3.750 0.0276 0.00798 0.00376 -0.0701 0.6354 0.0319 -3.500 0.0515 0.00742 0.00311 -0.0698 0.6243 0.0324 -3.000 0.0970 0.01453 0.00910 -0.0696 0.6184 0.0299 -2.750 0.1226 0.01324 0.00754 -0.0691 0.6066 0.0298 -2.500 0.1490 0.01234 0.00642 -0.0687 0.5945 0.0297 -2.250 0.1758 0.01166 0.00557 -0.0683 0.5822 0.0298 -2.000 0.2027 0.01112 0.00487 -0.0680 0.5703 0.0298 -1.750 0.2298 0.01080 0.00443 -0.0677 0.5586 0.0301 -1.500 0.2574 0.01062 0.00416 -0.0675 0.5480 0.0305 -1.250 0.2847 0.01034 0.00380 -0.0673 0.5385 0.0307 -1.000 0.3108 0.00967 0.00301 -0.0669 0.5295 0.0313 -0.750 0.3376 0.00931 0.00259 -0.0665 0.5210 0.0320 -0.500 0.3643 0.00913 0.00234 -0.0662 0.5124 0.0325 -0.250 0.3915 0.00897 0.00215 -0.0660 0.5047 0.0331 0.000 0.4185 0.00889 0.00201 -0.0658 0.4975 0.0337 0.250 0.4460 0.00878 0.00189 -0.0656 0.4914 0.0344 0.500 0.4731 0.00873 0.00180 -0.0654 0.4842 0.0353 0.750 0.5005 0.00868 0.00172 -0.0652 0.4778 0.0368 1.000 0.5279 0.00865 0.00166 -0.0651 0.4718 0.0381 1.250 0.5552 0.00864 0.00161 -0.0649 0.4659 0.0409 1.500 0.5825 0.00856 0.00161 -0.0647 0.4592 0.0591 1.750 0.6095 0.00857 0.00167 -0.0646 0.4527 0.0902 2.000 0.6373 0.00858 0.00170 -0.0645 0.4472 0.1002 2.250 0.6648 0.00859 0.00173 -0.0645 0.4422 0.1113 2.500 0.6919 0.00864 0.00179 -0.0643 0.4370 0.1234 2.750 0.7194 0.00859 0.00183 -0.0643 0.4325 0.1514 3.000 0.7452 0.00840 0.00195 -0.0640 0.4266 0.3060 3.250 0.8127 0.00721 0.00231 -0.0734 0.4186 0.9947 3.500 0.8717 0.00733 0.00238 -0.0805 0.4107 1.0000 3.750 0.8974 0.00743 0.00244 -0.0801 0.4049 1.0000 4.000 0.9233 0.00750 0.00251 -0.0798 0.3985 1.0000 4.250 0.9487 0.00762 0.00259 -0.0793 0.3903 1.0000 4.500 0.9738 0.00777 0.00267 -0.0788 0.3768 1.0000 4.750 0.9986 0.00794 0.00277 -0.0783 0.3558 1.0000 5.000 1.0214 0.00830 0.00294 -0.0775 0.3171 1.0000 5.250 1.0378 0.00932 0.00348 -0.0757 0.2319 1.0000 5.500 1.0590 0.00981 0.00381 -0.0746 0.2038 1.0000 5.750 1.0799 0.01029 0.00414 -0.0735 0.1732 1.0000 6.000 1.0980 0.01102 0.00458 -0.0720 0.1260 1.0000 6.250 1.1184 0.01149 0.00494 -0.0708 0.1068 1.0000 6.500 1.1391 0.01192 0.00527 -0.0696 0.0879 1.0000 6.750 1.1563 0.01261 0.00578 -0.0679 0.0579 1.0000 7.000 1.1769 0.01299 0.00614 -0.0667 0.0525 1.0000 7.250 1.1984 0.01329 0.00644 -0.0656 0.0479 1.0000 7.500 1.2193 0.01362 0.00675 -0.0645 0.0428 1.0000 7.750 1.2357 0.01426 0.00724 -0.0626 0.0223 1.0000 8.000 1.2528 0.01482 0.00781 -0.0608 0.0152 1.0000 8.250 1.2711 0.01529 0.00832 -0.0592 0.0136 1.0000 8.500 1.2892 0.01574 0.00882 -0.0576 0.0125 1.0000 8.750 1.3072 0.01616 0.00929 -0.0560 0.0121 1.0000 9.000 1.3239 0.01664 0.00983 -0.0543 0.0116 1.0000 9.250 1.3392 0.01719 0.01042 -0.0523 0.0111 1.0000 9.500 1.3528 0.01781 0.01109 -0.0500 0.0106 1.0000 9.750 1.3635 0.01854 0.01189 -0.0473 0.0102 1.0000 10.000 1.3664 0.01947 0.01290 -0.0433 0.0098 1.0000 10.250 1.3727 0.02037 0.01387 -0.0402 0.0095 1.0000 10.500 1.3848 0.02105 0.01461 -0.0382 0.0092 1.0000 10.750 1.3950 0.02190 0.01552 -0.0361 0.0089 1.0000 11.000 1.4035 0.02295 0.01663 -0.0340 0.0087 1.0000 11.250 1.4109 0.02416 0.01791 -0.0321 0.0084 1.0000 11.500 1.4175 0.02553 0.01936 -0.0303 0.0082 1.0000 11.750 1.4231 0.02711 0.02100 -0.0288 0.0080 1.0000 12.000 1.4275 0.02892 0.02290 -0.0276 0.0078 1.0000 12.250 1.4304 0.03103 0.02508 -0.0266 0.0076 1.0000 12.500 1.4309 0.03349 0.02764 -0.0257 0.0075 1.0000 12.750 1.4279 0.03644 0.03067 -0.0251 0.0073 1.0000 13.000 1.4208 0.03987 0.03420 -0.0245 0.0072 1.0000 13.250 1.4102 0.04373 0.03815 -0.0239 0.0071 1.0000 13.500 1.3990 0.04765 0.04217 -0.0233 0.0070 1.0000 13.750 1.4019 0.05019 0.04478 -0.0232 0.0069 1.0000 14.000 1.4036 0.05288 0.04756 -0.0232 0.0069 1.0000 14.250 1.4030 0.05587 0.05063 -0.0232 0.0068 1.0000 14.500 1.4020 0.05899 0.05383 -0.0233 0.0067 1.0000 14.750 1.4012 0.06214 0.05707 -0.0235 0.0066 1.0000 15.000 1.4001 0.06538 0.06039 -0.0237 0.0065 1.0000 15.250 1.3988 0.06870 0.06379 -0.0241 0.0064 1.0000 15.500 1.3971 0.07213 0.06729 -0.0246 0.0063 1.0000 15.750 1.3951 0.07563 0.07088 -0.0251 0.0061 1.0000 16.000 1.3927 0.07922 0.07454 -0.0257 0.0060 1.0000 16.250 1.3897 0.08292 0.07832 -0.0263 0.0059 1.0000 16.500 1.3867 0.08666 0.08213 -0.0270 0.0058 1.0000 16.750 1.3838 0.09039 0.08593 -0.0277 0.0057 1.0000 17.000 1.3802 0.09426 0.08988 -0.0286 0.0057 1.0000 17.250 1.3767 0.09818 0.09388 -0.0295 0.0056 1.0000 17.500 1.3734 0.10210 0.09787 -0.0305 0.0055 1.0000 17.750 1.3696 0.10614 0.10198 -0.0316 0.0055 1.0000 18.000 1.3660 0.11019 0.10611 -0.0329 0.0054 1.0000