XFOIL Version 6.94 Calculated polar for: GOE 497 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 0.6483 0.01057 0.00405 -0.1496 0.7310 0.4045 0.500 0.7040 0.01054 0.00401 -0.1491 0.7151 0.4387 1.000 0.7567 0.01051 0.00405 -0.1481 0.6968 0.4797 1.500 0.8092 0.01048 0.00411 -0.1471 0.6780 0.5203 2.000 0.8611 0.01044 0.00421 -0.1460 0.6578 0.5709 2.500 0.9106 0.01028 0.00439 -0.1444 0.6370 0.6741 4.500 1.0765 0.01175 0.00516 -0.1318 0.4452 1.0000 5.500 1.1528 0.01326 0.00627 -0.1253 0.3700 1.0000 6.000 1.1797 0.01419 0.00692 -0.1200 0.3084 1.0000 6.500 1.1895 0.01597 0.00815 -0.1123 0.2270 1.0000 7.000 1.2126 0.01741 0.00934 -0.1072 0.1836 1.0000 7.500 1.2194 0.01986 0.01123 -0.1003 0.0969 1.0000 8.000 1.2332 0.02211 0.01321 -0.0948 0.0510 1.0000 8.500 1.2395 0.02504 0.01588 -0.0890 0.0051 1.0000 9.000 1.2651 0.02683 0.01777 -0.0856 0.0044 1.0000 9.500 1.2890 0.02884 0.01993 -0.0824 0.0042 1.0000 10.000 1.3107 0.03113 0.02236 -0.0793 0.0041 1.0000 10.500 1.3297 0.03377 0.02517 -0.0762 0.0041 1.0000 11.000 1.3459 0.03680 0.02839 -0.0734 0.0041 1.0000 11.500 1.3589 0.04031 0.03211 -0.0708 0.0041 1.0000 12.000 1.3693 0.04432 0.03633 -0.0687 0.0041 1.0000 12.500 1.3766 0.04893 0.04118 -0.0669 0.0042 1.0000 13.000 1.3829 0.05397 0.04644 -0.0657 0.0042 1.0000 13.500 1.3864 0.05967 0.05237 -0.0650 0.0043 1.0000 14.000 1.3879 0.06599 0.05892 -0.0650 0.0043 1.0000 14.500 1.3863 0.07313 0.06631 -0.0657 0.0044 1.0000 15.000 1.3815 0.08119 0.07461 -0.0673 0.0045 1.0000 15.500 1.3740 0.09015 0.08382 -0.0696 0.0046 1.0000 16.000 1.3645 0.09984 0.09376 -0.0728 0.0047 1.0000 16.500 1.3540 0.10995 0.10410 -0.0765 0.0048 1.0000 17.000 1.3446 0.12004 0.11440 -0.0806 0.0049 1.0000 17.500 1.3374 0.12979 0.12434 -0.0849 0.0050 1.0000 18.000 1.3339 0.13878 0.13349 -0.0890 0.0051 1.0000 18.500 1.3352 0.14668 0.14151 -0.0927 0.0053 1.0000 19.000 1.3420 0.15314 0.14804 -0.0955 0.0054 1.0000 19.500 1.3617 0.15607 0.15094 -0.0958 0.0056 1.0000 20.000 1.3661 0.16355 0.15861 -0.1001 0.0058 1.0000 20.500 1.3648 0.17262 0.16796 -0.1057 0.0060 1.0000 21.000 1.3644 0.18127 0.17693 -0.1110 0.0063 1.0000 21.500 1.3615 0.19036 0.18630 -0.1169 0.0066 1.0000 22.000 1.3564 0.19998 0.19617 -0.1233 0.0069 1.0000 22.500 1.3494 0.21012 0.20654 -0.1303 0.0071 1.0000 23.000 1.3496 0.21811 0.21468 -0.1358 0.0074 1.0000 23.500 1.3271 0.23412 0.23101 -0.1473 0.0075 1.0000 24.500 0.9886 0.35256 0.35074 -0.1830 0.0196 1.0000 25.000 0.9862 0.36762 0.36580 -0.1886 0.0178 1.0000 25.500 0.9928 0.37614 0.37435 -0.1913 0.0168 1.0000 26.000 0.9964 0.38790 0.38612 -0.1947 0.0162 1.0000 26.500 1.0006 0.39894 0.39717 -0.1980 0.0147 1.0000 27.000 1.0065 0.40735 0.40561 -0.2006 0.0140 1.0000 27.500 1.0093 0.41974 0.41801 -0.2040 0.0135 1.0000 28.000 1.0129 0.43076 0.42906 -0.2072 0.0124 1.0000 28.500 1.0170 0.44016 0.43848 -0.2099 0.0117 1.0000 29.000 1.0226 0.44826 0.44661 -0.2118 0.0114 1.0000 29.500 1.0228 0.46208 0.46044 -0.2158 0.0110 1.0000 30.000 1.0255 0.47317 0.47156 -0.2188 0.0102 1.0000 30.500 1.0280 0.48312 0.48153 -0.2215 0.0098 1.0000 31.000 1.0303 0.49228 0.49072 -0.2241 0.0094 1.0000 31.500 1.0331 0.50088 0.49935 -0.2262 0.0092 1.0000 32.000 1.0335 0.51283 0.51132 -0.2294 0.0092 1.0000 32.500 1.0342 0.52465 0.52316 -0.2323 0.0090 1.0000 33.000 1.0350 0.53540 0.53394 -0.2350 0.0087 1.0000 33.500 1.0355 0.54525 0.54383 -0.2376 0.0085 1.0000 34.000 1.0356 0.55532 0.55392 -0.2402 0.0082 1.0000 34.500 1.0354 0.56509 0.56372 -0.2427 0.0080 1.0000 35.000 1.0349 0.57451 0.57317 -0.2452 0.0078 1.0000 35.500 1.0339 0.58372 0.58242 -0.2476 0.0077 1.0000 36.000 1.0328 0.59279 0.59151 -0.2500 0.0076 1.0000 36.500 1.0311 0.60159 0.60035 -0.2524 0.0075 1.0000 37.000 1.0292 0.61017 0.60896 -0.2546 0.0074 1.0000 39.000 1.0182 0.64530 0.64421 -0.2636 0.0073 1.0000 39.500 1.0148 0.65418 0.65313 -0.2658 0.0073 1.0000 40.000 1.0111 0.66293 0.66191 -0.2680 0.0072 1.0000 40.500 1.0073 0.67143 0.67045 -0.2701 0.0071 1.0000 41.000 1.0032 0.67990 0.67895 -0.2721 0.0068 1.0000 41.500 0.9986 0.68764 0.68672 -0.2740 0.0064 1.0000 42.000 0.9938 0.69504 0.69415 -0.2760 0.0061 1.0000 42.500 0.9884 0.70140 0.70054 -0.2779 0.0058 1.0000 43.000 0.9827 0.70723 0.70640 -0.2797 0.0057 1.0000 44.000 0.9716 0.72421 0.72343 -0.2832 0.0055 1.0000 44.500 0.9657 0.73149 0.73074 -0.2849 0.0051 1.0000 45.000 0.9593 0.73766 0.73694 -0.2865 0.0048 1.0000 45.500 0.9526 0.74323 0.74254 -0.2881 0.0045 1.0000 46.000 0.9453 0.74733 0.74667 -0.2898 0.0043 1.0000 47.000 0.9309 0.75962 0.75901 -0.2927 0.0041 1.0000 47.500 0.9238 0.76575 0.76516 -0.2940 0.0039 1.0000 48.000 0.9162 0.77085 0.77028 -0.2953 0.0036 1.0000 48.500 0.9082 0.77469 0.77415 -0.2967 0.0033 1.0000 49.000 0.8997 0.77753 0.77702 -0.2980 0.0031 1.0000 49.500 0.8907 0.77938 0.77889 -0.2993 0.0029 1.0000 50.500 0.8734 0.78706 0.78661 -0.3016 0.0028 1.0000 51.000 0.8649 0.79069 0.79026 -0.3026 0.0028 1.0000 51.500 0.8559 0.79328 0.79288 -0.3035 0.0026 1.0000 52.000 0.8466 0.79475 0.79437 -0.3045 0.0024 1.0000 52.500 0.8370 0.79590 0.79554 -0.3055 0.0022 1.0000 53.000 0.8271 0.79589 0.79556 -0.3064 0.0020 1.0000 53.500 0.8169 0.79520 0.79488 -0.3073 0.0019 1.0000 54.000 0.8062 0.79367 0.79337 -0.3082 0.0018 1.0000 55.500 0.7758 0.79393 0.79369 -0.3101 0.0017 1.0000 56.000 0.7655 0.79310 0.79288 -0.3107 0.0017 1.0000 56.500 0.7548 0.79112 0.79092 -0.3112 0.0016 1.0000 57.000 0.7441 0.78876 0.78857 -0.3117 0.0015 1.0000 57.500 0.7331 0.78567 0.78551 -0.3121 0.0014 1.0000 58.000 0.7219 0.78214 0.78200 -0.3125 0.0013 1.0000 58.500 0.7107 0.77816 0.77803 -0.3129 0.0012 1.0000 59.000 0.6992 0.77344 0.77333 -0.3132 0.0010 1.0000 59.500 0.6876 0.76822 0.76812 -0.3136 0.0010 1.0000 60.000 0.6758 0.76228 0.76220 -0.3139 0.0009 1.0000