XFOIL Version 6.96 Calculated polar for: GOE 308 (MVA H.40) 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.3241 0.09715 0.09503 -0.0280 1.0000 0.0204 -8.250 -0.3298 0.09499 0.09291 -0.0274 1.0000 0.0204 -8.000 -0.3413 0.09315 0.09113 -0.0258 1.0000 0.0205 -7.750 -0.3437 0.09042 0.08843 -0.0272 0.9985 0.0205 -7.500 -0.3171 0.08468 0.08266 -0.0360 0.9943 0.0206 -7.250 -0.3021 0.07816 0.07613 -0.0417 0.9897 0.0209 -7.000 -0.2810 0.07511 0.07308 -0.0432 0.9868 0.0215 -6.750 -0.2542 0.07129 0.06922 -0.0487 0.9838 0.0221 -6.500 -0.2318 0.06753 0.06544 -0.0535 0.9770 0.0230 -6.250 -0.1892 0.06205 0.05984 -0.0656 0.9718 0.0264 -6.000 -0.1620 0.05751 0.05521 -0.0707 0.9642 0.0266 -5.750 -0.1396 0.04946 0.04701 -0.0771 0.9587 0.0273 -5.500 -0.1172 0.04686 0.04436 -0.0787 0.9517 0.0280 -5.250 -0.0891 0.04466 0.04211 -0.0812 0.9459 0.0292 -5.000 -0.0589 0.04176 0.03911 -0.0842 0.9385 0.0315 -4.500 0.0005 0.03198 0.02881 -0.0898 0.9176 0.0368 -4.250 0.0281 0.03067 0.02741 -0.0909 0.9058 0.0384 -4.000 0.0557 0.02858 0.02513 -0.0916 0.8925 0.0418 -3.750 0.0787 0.02484 0.02103 -0.0913 0.8784 0.0479 -3.500 0.1035 0.02412 0.02021 -0.0912 0.8643 0.0500 -3.000 0.1403 0.01429 0.00894 -0.0863 0.8381 0.0408 -2.750 0.1649 0.01270 0.00694 -0.0852 0.8250 0.0397 -2.500 0.1903 0.01185 0.00585 -0.0844 0.8114 0.0396 -2.250 0.2156 0.01121 0.00503 -0.0836 0.7976 0.0398 -2.000 0.2408 0.01073 0.00442 -0.0828 0.7830 0.0404 -1.750 0.2657 0.01035 0.00392 -0.0819 0.7671 0.0415 -1.500 0.2902 0.00999 0.00344 -0.0810 0.7502 0.0420 -1.250 0.3144 0.00970 0.00305 -0.0800 0.7316 0.0428 -1.000 0.3380 0.00949 0.00274 -0.0788 0.7103 0.0435 -0.750 0.3614 0.00936 0.00248 -0.0777 0.6876 0.0442 -0.500 0.3844 0.00928 0.00227 -0.0765 0.6634 0.0449 -0.250 0.4076 0.00924 0.00211 -0.0753 0.6400 0.0458 0.000 0.4304 0.00921 0.00195 -0.0741 0.6173 0.0492 0.250 0.4536 0.00921 0.00187 -0.0730 0.5942 0.0539 0.500 0.4765 0.00923 0.00192 -0.0718 0.5716 0.0852 0.750 0.5007 0.00936 0.00198 -0.0710 0.5496 0.1045 1.000 0.5244 0.00948 0.00202 -0.0701 0.5297 0.1151 1.250 0.5485 0.00961 0.00205 -0.0693 0.5119 0.1221 1.500 0.5722 0.00967 0.00207 -0.0684 0.4960 0.1296 1.750 0.5962 0.00978 0.00211 -0.0676 0.4823 0.1376 2.000 0.6201 0.00985 0.00217 -0.0668 0.4701 0.1481 2.250 0.6447 0.00991 0.00224 -0.0661 0.4600 0.1609 2.500 0.6687 0.00997 0.00234 -0.0654 0.4512 0.1900 2.750 0.6863 0.00944 0.00248 -0.0635 0.4437 0.4922 3.000 0.7968 0.00898 0.00304 -0.0817 0.4287 0.9915 3.250 0.8625 0.00917 0.00316 -0.0903 0.4191 1.0000 3.500 0.8850 0.00930 0.00326 -0.0892 0.4132 1.0000 3.750 0.9071 0.00946 0.00338 -0.0880 0.4078 1.0000 4.000 0.9299 0.00955 0.00349 -0.0870 0.4021 1.0000 4.250 0.9517 0.00971 0.00363 -0.0858 0.3966 1.0000 4.500 0.9738 0.00985 0.00377 -0.0847 0.3912 1.0000 4.750 0.9958 0.00997 0.00391 -0.0835 0.3851 1.0000 5.000 1.0169 0.01011 0.00404 -0.0822 0.3762 1.0000 5.250 1.0377 0.01026 0.00417 -0.0808 0.3660 1.0000 5.500 1.0592 0.01036 0.00430 -0.0795 0.3567 1.0000 5.750 1.0798 0.01052 0.00445 -0.0781 0.3471 1.0000 6.000 1.0999 0.01069 0.00460 -0.0766 0.3345 1.0000 6.250 1.1200 0.01087 0.00478 -0.0751 0.3211 1.0000 6.500 1.1396 0.01108 0.00496 -0.0735 0.3030 1.0000 6.750 1.1569 0.01142 0.00518 -0.0716 0.2756 1.0000 7.000 1.1701 0.01202 0.00554 -0.0690 0.2298 1.0000 7.250 1.1775 0.01304 0.00617 -0.0654 0.1706 1.0000 7.500 1.1745 0.01475 0.00722 -0.0602 0.0749 1.0000 7.750 1.1763 0.01612 0.00835 -0.0556 0.0257 1.0000 8.000 1.1916 0.01662 0.00893 -0.0534 0.0231 1.0000 8.250 1.2044 0.01725 0.00963 -0.0507 0.0209 1.0000 8.500 1.2137 0.01807 0.01057 -0.0474 0.0193 1.0000 8.750 1.2230 0.01870 0.01127 -0.0441 0.0187 1.0000 9.000 1.2314 0.01934 0.01199 -0.0407 0.0180 1.0000 9.250 1.2395 0.02003 0.01278 -0.0375 0.0173 1.0000 9.500 1.2470 0.02082 0.01363 -0.0343 0.0164 1.0000 9.750 1.2531 0.02172 0.01460 -0.0311 0.0156 1.0000 10.000 1.2546 0.02293 0.01590 -0.0275 0.0150 1.0000 10.250 1.2541 0.02435 0.01741 -0.0239 0.0146 1.0000 10.500 1.2503 0.02610 0.01927 -0.0204 0.0143 1.0000 10.750 1.2398 0.02853 0.02182 -0.0167 0.0139 1.0000 11.000 1.2398 0.03041 0.02378 -0.0145 0.0139 1.0000 11.250 1.2478 0.03175 0.02523 -0.0131 0.0135 1.0000 11.500 1.2496 0.03370 0.02726 -0.0114 0.0134 1.0000 11.750 1.2523 0.03567 0.02932 -0.0099 0.0131 1.0000 12.000 1.2567 0.03755 0.03129 -0.0088 0.0126 1.0000 12.250 1.2599 0.03961 0.03343 -0.0078 0.0122 1.0000 12.500 1.2621 0.04185 0.03575 -0.0066 0.0121 1.0000 12.750 1.2661 0.04393 0.03790 -0.0059 0.0118 1.0000 13.000 1.2693 0.04615 0.04019 -0.0050 0.0116 1.0000 13.250 1.2724 0.04841 0.04252 -0.0042 0.0112 1.0000 13.500 1.2761 0.05065 0.04484 -0.0034 0.0110 1.0000 13.750 1.2798 0.05291 0.04715 -0.0026 0.0108 1.0000 14.000 1.2850 0.05508 0.04939 -0.0016 0.0106 1.0000 14.250 1.2971 0.05688 0.05120 0.0005 0.0103 1.0000 14.500 1.2981 0.05948 0.05395 0.0006 0.0104 1.0000 14.750 1.3061 0.06196 0.05653 0.0020 0.0103 1.0000 15.000 1.3087 0.06495 0.05966 0.0027 0.0103 1.0000 15.250 1.3076 0.06835 0.06322 0.0030 0.0103 1.0000 15.500 1.3004 0.07191 0.06697 0.0023 0.0105 1.0000 15.750 1.2957 0.07611 0.07133 0.0024 0.0104 1.0000