XFOIL Version 6.94 Calculated polar for: GOE 233 (MVA CA4) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 1.000 1.0496 0.01108 0.00471 -0.2136 0.6319 0.3404 1.500 1.1051 0.01135 0.00499 -0.2132 0.6198 0.3461 2.000 1.1604 0.01161 0.00524 -0.2128 0.6066 0.3543 2.500 1.2162 0.01177 0.00538 -0.2126 0.5932 0.3597 3.000 1.2709 0.01194 0.00556 -0.2122 0.5795 0.3645 3.500 1.3203 0.01220 0.00564 -0.2107 0.5292 0.3699 4.000 1.3653 0.01299 0.00598 -0.2086 0.4523 0.3753 4.500 1.4095 0.01392 0.00655 -0.2066 0.3894 0.3794 5.000 1.4462 0.01542 0.00752 -0.2036 0.2920 0.3830 5.500 1.4727 0.01766 0.00911 -0.1990 0.1951 0.3866 6.500 1.4990 0.02246 0.01295 -0.1852 0.0302 0.3937 7.000 1.5193 0.02447 0.01486 -0.1799 0.0030 0.3970 7.500 1.5493 0.02589 0.01639 -0.1764 0.0024 0.4020 8.000 1.5770 0.02757 0.01821 -0.1727 0.0022 0.4061 8.500 1.6020 0.02956 0.02035 -0.1690 0.0022 0.4106 9.000 1.6243 0.03190 0.02284 -0.1653 0.0022 0.4146 9.500 1.6441 0.03458 0.02571 -0.1617 0.0022 0.4187 10.000 1.6607 0.03767 0.02900 -0.1582 0.0023 0.4236 10.500 1.6743 0.04120 0.03274 -0.1548 0.0023 0.4287 11.000 1.6849 0.04517 0.03690 -0.1515 0.0024 0.4330 11.500 1.6931 0.04956 0.04150 -0.1485 0.0025 0.4371 12.000 1.6994 0.05443 0.04662 -0.1459 0.0026 0.4420 12.500 1.7023 0.05990 0.05233 -0.1436 0.0026 0.4469 13.000 1.7019 0.06606 0.05873 -0.1417 0.0027 0.4522 13.500 1.6982 0.07287 0.06578 -0.1402 0.0028 0.4578 14.000 1.6908 0.08045 0.07363 -0.1392 0.0029 0.4638 14.500 1.6784 0.08898 0.08242 -0.1388 0.0030 0.4694 15.500 1.6424 0.10869 0.10261 -0.1403 0.0031 0.4809 16.000 1.6284 0.11832 0.11247 -0.1420 0.0032 0.4892 16.500 1.6247 0.12649 0.12087 -0.1438 0.0033 0.5031 18.500 1.6063 0.15988 0.15542 -0.1550 0.0040 1.0000 19.000 1.6070 0.16688 0.16250 -0.1578 0.0043 1.0000 19.500 1.6166 0.17165 0.16729 -0.1591 0.0045 1.0000 20.000 1.6179 0.18022 0.17614 -0.1642 0.0048 1.0000 20.500 1.6211 0.18756 0.18377 -0.1682 0.0053 1.0000 21.500 1.6333 0.20019 0.19679 -0.1753 0.0062 1.0000 22.000 1.6179 0.21346 0.21057 -0.1851 0.0068 1.0000 22.500 1.6012 0.22718 0.22467 -0.1958 0.0072 1.0000 23.000 1.5941 0.23799 0.23570 -0.2042 0.0078 1.0000 23.500 1.5682 0.25807 0.25615 -0.2209 0.0078 1.0000 25.500 0.9779 0.33608 0.33466 -0.1816 0.0133 1.0000 26.000 0.9805 0.34284 0.34143 -0.1833 0.0124 1.0000 27.000 0.9818 0.36014 0.35873 -0.1875 0.0104 1.0000 28.000 0.9838 0.37643 0.37504 -0.1914 0.0090 1.0000 28.500 0.9850 0.38373 0.38235 -0.1932 0.0081 1.0000 29.500 0.9861 0.39989 0.39854 -0.1970 0.0072 1.0000 30.000 0.9867 0.40775 0.40641 -0.1989 0.0065 1.0000 30.500 0.9872 0.41428 0.41296 -0.2006 0.0061 1.0000 31.000 0.9884 0.41930 0.41800 -0.2018 0.0059 1.0000 31.500 0.9868 0.42984 0.42855 -0.2042 0.0058 1.0000 32.000 0.9864 0.43859 0.43732 -0.2061 0.0053 1.0000 32.500 0.9859 0.44594 0.44469 -0.2079 0.0050 1.0000 33.000 0.9852 0.45289 0.45165 -0.2097 0.0048 1.0000 33.500 0.9843 0.45933 0.45812 -0.2114 0.0046 1.0000 34.000 0.9832 0.46507 0.46388 -0.2130 0.0045 1.0000 34.500 0.9819 0.47138 0.47021 -0.2145 0.0044 1.0000 35.000 0.9797 0.47933 0.47819 -0.2164 0.0044 1.0000 35.500 0.9777 0.48699 0.48586 -0.2183 0.0044 1.0000 36.000 0.9756 0.49444 0.49334 -0.2201 0.0043 1.0000 36.500 0.9734 0.50152 0.50044 -0.2219 0.0043 1.0000 37.000 0.9708 0.50816 0.50711 -0.2236 0.0042 1.0000 37.500 0.9681 0.51468 0.51365 -0.2253 0.0042 1.0000 38.000 0.9651 0.52086 0.51986 -0.2269 0.0041 1.0000 38.500 0.9618 0.52689 0.52591 -0.2286 0.0040 1.0000 39.000 0.9582 0.53271 0.53176 -0.2302 0.0040 1.0000 39.500 0.9545 0.53846 0.53754 -0.2319 0.0039 1.0000 40.000 0.9505 0.54399 0.54309 -0.2335 0.0039 1.0000 40.500 0.9463 0.54939 0.54853 -0.2351 0.0038 1.0000 41.000 0.9419 0.55450 0.55366 -0.2367 0.0036 1.0000 41.500 0.9372 0.55942 0.55861 -0.2383 0.0035 1.0000 42.000 0.9322 0.56399 0.56320 -0.2399 0.0033 1.0000 42.500 0.9268 0.56783 0.56708 -0.2415 0.0032 1.0000 43.500 0.9162 0.57946 0.57875 -0.2444 0.0031 1.0000 44.000 0.9113 0.58555 0.58486 -0.2458 0.0028 1.0000 44.500 0.9056 0.59038 0.58971 -0.2473 0.0025 1.0000 45.000 0.8995 0.59422 0.59358 -0.2487 0.0023 1.0000 45.500 0.8929 0.59738 0.59677 -0.2502 0.0022 1.0000 47.000 0.8735 0.61104 0.61049 -0.2542 0.0020 1.0000 47.500 0.8672 0.61574 0.61521 -0.2554 0.0018 1.0000 48.000 0.8602 0.61919 0.61868 -0.2567 0.0016 1.0000 48.500 0.8527 0.62182 0.62134 -0.2580 0.0014 1.0000 49.000 0.8449 0.62352 0.62306 -0.2594 0.0013 1.0000 49.500 0.8363 0.62442 0.62398 -0.2608 0.0012 1.0000 50.500 0.8211 0.63155 0.63115 -0.2631 0.0012 1.0000 51.000 0.8137 0.63517 0.63479 -0.2642 0.0012 1.0000 51.500 0.8059 0.63785 0.63749 -0.2652 0.0011 1.0000 52.000 0.7979 0.64007 0.63973 -0.2663 0.0010 1.0000 52.500 0.7894 0.64155 0.64123 -0.2674 0.0009 1.0000 53.000 0.7806 0.64233 0.64203 -0.2685 0.0008 1.0000 53.500 0.7717 0.64291 0.64263 -0.2697 0.0007 1.0000 54.000 0.7625 0.64299 0.64274 -0.2708 0.0006 1.0000 54.500 0.7530 0.64250 0.64226 -0.2719 0.0006 1.0000 55.000 0.7431 0.64136 0.64114 -0.2731 0.0006 1.0000 56.000 0.7248 0.64322 0.64303 -0.2749 0.0005 1.0000 56.500 0.7159 0.64374 0.64357 -0.2757 0.0005 1.0000 57.000 0.7063 0.64317 0.64302 -0.2766 0.0004 1.0000 57.500 0.6965 0.64204 0.64192 -0.2776 0.0004 1.0000 58.000 0.6864 0.64032 0.64021 -0.2785 0.0003 1.0000 58.500 0.6762 0.63833 0.63824 -0.2795 0.0003 1.0000