XFOIL Version 6.96 Calculated polar for: GOE 165 (MVA MK.11) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.3049 0.09443 0.09013 -0.0352 1.0000 0.0261 -7.750 -0.3085 0.09214 0.08792 -0.0339 1.0000 0.0256 -7.500 -0.3158 0.08987 0.08575 -0.0323 1.0000 0.0252 -7.250 -0.3270 0.08776 0.08375 -0.0304 1.0000 0.0249 -7.000 -0.3212 0.08354 0.07959 -0.0339 0.9959 0.0245 -6.750 -0.2998 0.07688 0.07295 -0.0430 0.9880 0.0241 -6.500 -0.2770 0.06883 0.06490 -0.0542 0.9787 0.0235 -6.250 -0.2469 0.05605 0.05197 -0.0746 0.9675 0.0223 -5.750 -0.1420 0.03576 0.03012 -0.1149 0.9481 0.0215 -5.500 -0.0949 0.03138 0.02505 -0.1220 0.9431 0.0211 -5.250 -0.0568 0.02846 0.02160 -0.1253 0.9339 0.0210 -5.000 -0.0143 0.02603 0.01882 -0.1286 0.9279 0.0213 -4.750 0.0207 0.02425 0.01685 -0.1300 0.9167 0.0218 -4.500 0.0571 0.02286 0.01533 -0.1314 0.9059 0.0236 -4.250 0.0959 0.02172 0.01408 -0.1330 0.8961 0.0259 -4.000 0.1345 0.02072 0.01296 -0.1349 0.8840 0.0274 -3.750 0.1749 0.01974 0.01181 -0.1376 0.8708 0.0304 -3.500 0.2168 0.01882 0.01066 -0.1407 0.8576 0.0384 -3.250 0.2608 0.01754 0.00909 -0.1443 0.8441 0.0596 -3.000 0.3033 0.01628 0.00875 -0.1482 0.8295 0.2939 -2.750 0.3404 0.01653 0.00876 -0.1494 0.8122 0.3374 -2.250 0.4107 0.01708 0.00885 -0.1510 0.7753 0.3712 -2.000 0.4447 0.01712 0.00858 -0.1519 0.7581 0.3814 -1.750 0.4759 0.01734 0.00866 -0.1521 0.7426 0.3902 -1.500 0.5066 0.01752 0.00867 -0.1523 0.7276 0.3999 -1.250 0.5374 0.01763 0.00855 -0.1527 0.7133 0.4098 -1.000 0.5663 0.01772 0.00854 -0.1527 0.6996 0.4147 -0.750 0.5952 0.01778 0.00845 -0.1527 0.6857 0.4204 -0.500 0.6240 0.01783 0.00831 -0.1528 0.6713 0.4267 -0.250 0.6510 0.01792 0.00832 -0.1525 0.6564 0.4310 0.000 0.6781 0.01800 0.00827 -0.1522 0.6409 0.4365 0.250 0.7050 0.01806 0.00821 -0.1519 0.6246 0.4418 0.500 0.7306 0.01814 0.00825 -0.1513 0.6077 0.4457 0.750 0.7562 0.01822 0.00826 -0.1508 0.5889 0.4507 1.000 0.7819 0.01831 0.00824 -0.1503 0.5673 0.4562 1.250 0.8063 0.01839 0.00829 -0.1495 0.5412 0.4598 1.500 0.8307 0.01852 0.00830 -0.1488 0.5113 0.4639 1.750 0.8549 0.01871 0.00829 -0.1480 0.4829 0.4684 2.250 0.9030 0.01923 0.00848 -0.1466 0.4452 0.4748 2.500 0.9276 0.01951 0.00867 -0.1460 0.4327 0.4784 2.750 0.9528 0.01981 0.00888 -0.1456 0.4218 0.4823 3.000 0.9777 0.02015 0.00913 -0.1451 0.4111 0.4857 3.500 1.0261 0.02079 0.00970 -0.1439 0.3892 0.4917 3.750 1.0506 0.02112 0.01001 -0.1434 0.3790 0.4955 4.000 1.0748 0.02150 0.01030 -0.1428 0.3697 0.4992 4.250 1.0994 0.02175 0.01063 -0.1423 0.3609 0.5021 4.500 1.1234 0.02210 0.01097 -0.1417 0.3537 0.5051 4.750 1.1481 0.02237 0.01134 -0.1411 0.3467 0.5087 5.000 1.1726 0.02271 0.01171 -0.1406 0.3416 0.5128 5.250 1.1972 0.02304 0.01211 -0.1401 0.3369 0.5166 5.500 1.2215 0.02332 0.01257 -0.1395 0.3317 0.5206 5.750 1.2454 0.02367 0.01299 -0.1389 0.3266 0.5249 6.000 1.2691 0.02403 0.01344 -0.1382 0.3214 0.5291 6.250 1.2892 0.02431 0.01381 -0.1370 0.3098 0.5328 6.500 1.3071 0.02458 0.01415 -0.1353 0.2923 0.5372 6.750 1.3263 0.02488 0.01459 -0.1339 0.2753 0.5425 7.000 1.3457 0.02520 0.01502 -0.1326 0.2568 0.5478 7.250 1.3648 0.02560 0.01550 -0.1313 0.2364 0.5539 7.500 1.3790 0.02633 0.01605 -0.1293 0.1885 0.5600 7.750 1.3738 0.02895 0.01783 -0.1250 0.1039 0.5644 8.000 1.3763 0.03085 0.01951 -0.1216 0.0563 0.5701 8.250 1.3867 0.03192 0.02074 -0.1191 0.0466 0.5773 8.500 1.4000 0.03277 0.02180 -0.1170 0.0240 0.5869 8.750 1.4019 0.03449 0.02353 -0.1138 0.0209 0.5974 9.000 1.4084 0.03584 0.02508 -0.1111 0.0190 0.6148 9.250 1.4131 0.03700 0.02677 -0.1083 0.0178 0.7084 9.500 1.4116 0.03846 0.02850 -0.1048 0.0172 1.0000 9.750 1.4127 0.04044 0.03070 -0.1022 0.0164 1.0000 10.000 1.4114 0.04273 0.03321 -0.0999 0.0157 1.0000 10.250 1.4081 0.04536 0.03607 -0.0979 0.0151 1.0000 10.500 1.4028 0.04839 0.03932 -0.0963 0.0147 1.0000 10.750 1.3960 0.05183 0.04299 -0.0953 0.0145 1.0000 11.000 1.3869 0.05584 0.04723 -0.0948 0.0143 1.0000 11.250 1.3761 0.06036 0.05197 -0.0949 0.0141 1.0000 11.500 1.3635 0.06539 0.05722 -0.0954 0.0140 1.0000 11.750 1.3491 0.07090 0.06294 -0.0964 0.0140 1.0000 12.000 1.3335 0.07684 0.06908 -0.0977 0.0139 1.0000 12.250 1.3175 0.08312 0.07555 -0.0994 0.0139 1.0000 12.500 1.3024 0.08948 0.08209 -0.1013 0.0139 1.0000 12.750 1.2887 0.09574 0.08852 -0.1031 0.0138 1.0000