XFOIL Version 6.94 Calculated polar for: GOE 510 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5148 0.01280 0.00471 -0.0982 0.6349 0.0839 0.500 0.5497 0.01267 0.00448 -0.0935 0.6050 0.0891 1.000 0.5784 0.01265 0.00436 -0.0875 0.5747 0.0971 1.500 0.6038 0.01254 0.00433 -0.0810 0.5453 0.1335 2.000 0.6335 0.01263 0.00466 -0.0756 0.5195 0.2666 2.500 0.6678 0.01296 0.00491 -0.0711 0.4976 0.3047 3.500 0.7410 0.01347 0.00536 -0.0635 0.4646 0.3698 4.000 0.7660 0.01309 0.00555 -0.0574 0.4528 0.6061 4.500 1.0052 0.01435 0.00722 -0.0973 0.4072 1.0000 5.000 1.0157 0.01473 0.00745 -0.0885 0.3842 1.0000 5.500 1.0412 0.01504 0.00776 -0.0827 0.3721 1.0000 6.000 1.0564 0.01554 0.00811 -0.0752 0.3470 1.0000 6.500 1.0808 0.01606 0.00857 -0.0695 0.3306 1.0000 7.000 1.1030 0.01673 0.00913 -0.0637 0.3078 1.0000 7.500 1.1213 0.01769 0.00992 -0.0576 0.2778 1.0000 8.000 1.1358 0.01903 0.01102 -0.0513 0.2390 1.0000 8.500 1.1476 0.02076 0.01249 -0.0451 0.1972 1.0000 9.000 1.1412 0.02374 0.01501 -0.0374 0.1267 1.0000 9.500 1.1013 0.02935 0.02006 -0.0273 0.0083 1.0000 10.000 1.1209 0.03148 0.02228 -0.0241 0.0070 1.0000 10.500 1.1387 0.03389 0.02481 -0.0211 0.0067 1.0000 11.000 1.1537 0.03672 0.02779 -0.0183 0.0064 1.0000 11.500 1.1656 0.04001 0.03125 -0.0158 0.0063 1.0000 12.000 1.1751 0.04377 0.03519 -0.0137 0.0063 1.0000 12.500 1.1811 0.04812 0.03973 -0.0121 0.0062 1.0000 13.000 1.1842 0.05301 0.04482 -0.0108 0.0062 1.0000 13.500 1.1826 0.05872 0.05076 -0.0100 0.0063 1.0000 14.000 1.1775 0.06511 0.05738 -0.0097 0.0063 1.0000 14.500 1.1689 0.07228 0.06479 -0.0099 0.0064 1.0000 15.000 1.1567 0.08024 0.07300 -0.0108 0.0065 1.0000 15.500 1.1426 0.08873 0.08173 -0.0121 0.0065 1.0000 16.000 1.1264 0.09773 0.09095 -0.0139 0.0066 1.0000 16.500 1.1056 0.10768 0.10113 -0.0162 0.0067 1.0000 17.000 1.0919 0.11669 0.11032 -0.0186 0.0068 1.0000 17.500 1.0791 0.12568 0.11946 -0.0212 0.0069 1.0000 18.000 1.0729 0.13363 0.12753 -0.0237 0.0070 1.0000 18.500 1.0721 0.14054 0.13453 -0.0258 0.0071 1.0000 19.000 1.0771 0.14635 0.14039 -0.0277 0.0072 1.0000 19.500 1.0928 0.14961 0.14361 -0.0282 0.0075 1.0000 20.000 1.1156 0.15137 0.14534 -0.0279 0.0077 1.0000 20.500 1.1273 0.15635 0.15048 -0.0300 0.0080 1.0000 21.000 1.1560 0.15699 0.15124 -0.0288 0.0088 1.0000 21.500 1.2159 0.15030 0.14435 -0.0224 0.0098 1.0000 22.000 0.9530 0.15114 0.14660 -0.0294 0.0094 1.0000 22.500 0.9694 0.15364 0.14940 -0.0309 0.0108 1.0000 23.000 1.0216 0.14978 0.14569 -0.0271 0.0150 1.0000 24.000 0.7656 0.23934 0.23687 -0.0735 0.0368 1.0000 24.500 0.7681 0.24793 0.24547 -0.0778 0.0330 1.0000 25.500 0.7791 0.26311 0.26070 -0.0855 0.0284 1.0000 26.000 0.7790 0.27359 0.27119 -0.0903 0.0259 1.0000 26.500 1.0607 0.28669 0.28356 -0.0992 0.0252 1.0000 27.000 1.0756 0.28959 0.28649 -0.1018 0.0244 1.0000 27.500 0.7950 0.29733 0.29501 -0.1015 0.0214 1.0000 28.000 0.8069 0.30176 0.29949 -0.1038 0.0208 1.0000 28.500 0.8027 0.31506 0.31278 -0.1093 0.0191 1.0000 29.000 0.8087 0.32210 0.31987 -0.1127 0.0182 1.0000 29.500 0.8173 0.32750 0.32531 -0.1154 0.0177 1.0000 30.000 0.8175 0.33840 0.33623 -0.1198 0.0172 1.0000 30.500 0.8208 0.34728 0.34514 -0.1235 0.0161 1.0000 31.000 0.8253 0.35469 0.35258 -0.1269 0.0154 1.0000 31.500 0.8306 0.36111 0.35904 -0.1301 0.0149 1.0000 32.000 0.8378 0.36662 0.36459 -0.1326 0.0147 1.0000 32.500 0.8376 0.37671 0.37470 -0.1367 0.0145 1.0000 33.000 0.8390 0.38603 0.38406 -0.1405 0.0142 1.0000 33.500 0.8414 0.39415 0.39221 -0.1439 0.0137 1.0000 34.000 0.8439 0.40179 0.39989 -0.1471 0.0133 1.0000 34.500 0.8462 0.40910 0.40724 -0.1504 0.0130 1.0000 35.000 0.8482 0.41623 0.41441 -0.1536 0.0127 1.0000 35.500 0.8499 0.42309 0.42131 -0.1567 0.0125 1.0000 36.000 0.8515 0.42963 0.42789 -0.1597 0.0123 1.0000 36.500 0.8533 0.43569 0.43400 -0.1626 0.0121 1.0000 37.500 0.8543 0.44978 0.44816 -0.1686 0.0120 1.0000 38.000 0.8532 0.45784 0.45625 -0.1719 0.0119 1.0000 38.500 0.8523 0.46598 0.46443 -0.1750 0.0117 1.0000 39.000 0.8517 0.47335 0.47185 -0.1779 0.0111 1.0000 39.500 0.8508 0.47990 0.47844 -0.1807 0.0105 1.0000 40.000 0.8498 0.48574 0.48432 -0.1835 0.0100 1.0000 40.500 0.8488 0.49074 0.48936 -0.1861 0.0098 1.0000 41.000 0.8462 0.49965 0.49830 -0.1890 0.0096 1.0000 41.500 0.8441 0.50747 0.50616 -0.1916 0.0088 1.0000 42.000 0.8418 0.51351 0.51224 -0.1942 0.0081 1.0000 42.500 0.8391 0.51856 0.51732 -0.1968 0.0078 1.0000 43.500 0.8330 0.53285 0.53168 -0.2017 0.0072 1.0000 44.000 0.8295 0.53886 0.53773 -0.2041 0.0065 1.0000 44.500 0.8257 0.54373 0.54263 -0.2065 0.0061 1.0000 45.000 0.8215 0.54749 0.54643 -0.2088 0.0058 1.0000 45.500 0.8171 0.55376 0.55272 -0.2111 0.0057 1.0000 46.000 0.8130 0.56108 0.56007 -0.2131 0.0052 1.0000 46.500 0.8083 0.56590 0.56493 -0.2153 0.0048 1.0000 47.000 0.8031 0.56978 0.56884 -0.2174 0.0044 1.0000 47.500 0.7975 0.57254 0.57164 -0.2195 0.0041 1.0000 48.500 0.7866 0.58327 0.58241 -0.2233 0.0039 1.0000 49.000 0.7808 0.58734 0.58651 -0.2251 0.0035 1.0000 49.500 0.7746 0.59055 0.58975 -0.2269 0.0031 1.0000 50.000 0.7679 0.59281 0.59204 -0.2287 0.0028 1.0000 50.500 0.7609 0.59417 0.59343 -0.2305 0.0027 1.0000 51.500 0.7468 0.59975 0.59905 -0.2337 0.0025 1.0000 52.000 0.7398 0.60255 0.60188 -0.2351 0.0025 1.0000 52.500 0.7327 0.60471 0.60407 -0.2365 0.0023 1.0000 53.000 0.7250 0.60599 0.60537 -0.2378 0.0020 1.0000 53.500 0.7171 0.60666 0.60607 -0.2392 0.0017 1.0000 54.000 0.7089 0.60639 0.60582 -0.2405 0.0015 1.0000 54.500 0.7003 0.60551 0.60496 -0.2418 0.0014 1.0000 55.000 0.6911 0.60364 0.60312 -0.2431 0.0013 1.0000 55.500 0.6829 0.60493 0.60443 -0.2441 0.0012 1.0000 56.000 0.6747 0.60512 0.60464 -0.2450 0.0010 1.0000 56.500 0.6658 0.60383 0.60337 -0.2459 0.0009 1.0000 57.000 0.6566 0.60159 0.60115 -0.2469 0.0007 1.0000 58.000 0.6379 0.59765 0.59725 -0.2484 0.0006 1.0000 58.500 0.6285 0.59519 0.59480 -0.2491 0.0005 1.0000 59.000 0.6189 0.59210 0.59174 -0.2498 0.0003 1.0000 59.500 0.6089 0.58811 0.58776 -0.2504 0.0001 1.0000