XFOIL Version 6.94 Calculated polar for: GOE 567 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 0.6284 0.01161 0.00462 -0.1443 0.6431 0.4697 0.500 0.6822 0.01163 0.00466 -0.1436 0.6291 0.4953 1.000 0.7366 0.01175 0.00480 -0.1431 0.6171 0.5210 1.500 0.7903 0.01181 0.00487 -0.1425 0.6044 0.5450 2.000 0.8442 0.01195 0.00507 -0.1420 0.5929 0.5681 2.500 0.8974 0.01203 0.00519 -0.1413 0.5804 0.5928 3.000 0.9484 0.01209 0.00534 -0.1402 0.5652 0.6199 4.000 1.0288 0.01215 0.00523 -0.1336 0.4859 0.6969 5.000 1.1060 0.01261 0.00584 -0.1268 0.4050 1.0000 5.500 1.1309 0.01365 0.00649 -0.1214 0.3410 1.0000 6.000 1.1369 0.01535 0.00767 -0.1130 0.2560 1.0000 6.500 1.1147 0.01867 0.01018 -0.1014 0.1225 1.0000 7.000 1.1306 0.02052 0.01188 -0.0962 0.0936 1.0000 7.500 1.1415 0.02284 0.01400 -0.0909 0.0485 1.0000 8.000 1.1601 0.02495 0.01610 -0.0870 0.0339 1.0000 8.500 1.1686 0.02797 0.01904 -0.0827 0.0054 1.0000 9.000 1.1894 0.03038 0.02154 -0.0799 0.0048 1.0000 9.500 1.2088 0.03306 0.02434 -0.0774 0.0046 1.0000 10.000 1.2262 0.03607 0.02749 -0.0750 0.0045 1.0000 10.500 1.2415 0.03941 0.03099 -0.0729 0.0045 1.0000 11.000 1.2545 0.04316 0.03491 -0.0710 0.0045 1.0000 11.500 1.2655 0.04733 0.03925 -0.0694 0.0045 1.0000 12.000 1.2742 0.05197 0.04408 -0.0682 0.0046 1.0000 12.500 1.2813 0.05706 0.04937 -0.0673 0.0046 1.0000 13.000 1.2885 0.06239 0.05489 -0.0668 0.0047 1.0000 13.500 1.2947 0.06810 0.06079 -0.0668 0.0047 1.0000 14.000 1.3007 0.07408 0.06695 -0.0671 0.0048 1.0000 14.500 1.3049 0.08056 0.07363 -0.0678 0.0049 1.0000 15.000 1.3074 0.08752 0.08078 -0.0689 0.0051 1.0000 15.500 1.3073 0.09508 0.08854 -0.0705 0.0052 1.0000 16.000 1.3057 0.10309 0.09675 -0.0726 0.0053 1.0000 16.500 1.3039 0.11122 0.10505 -0.0749 0.0055 1.0000 17.000 1.3039 0.11912 0.11310 -0.0775 0.0056 1.0000 17.500 1.3067 0.12642 0.12051 -0.0799 0.0058 1.0000 18.000 1.3152 0.13239 0.12654 -0.0817 0.0060 1.0000 18.500 1.3375 0.13523 0.12933 -0.0815 0.0062 1.0000 19.000 1.3427 0.14257 0.13692 -0.0850 0.0065 1.0000 19.500 1.3520 0.14885 0.14347 -0.0877 0.0069 1.0000 20.000 1.3647 0.15399 0.14882 -0.0895 0.0074 1.0000 21.000 1.3906 0.16386 0.15904 -0.0936 0.0083 1.0000 21.500 1.3699 0.17677 0.17251 -0.1018 0.0089 1.0000 22.000 1.3519 0.18905 0.18520 -0.1098 0.0093 1.0000 22.500 1.3348 0.20134 0.19780 -0.1182 0.0097 1.0000 23.000 1.3321 0.20998 0.20662 -0.1239 0.0102 1.0000 23.500 1.2967 0.22878 0.22578 -0.1373 0.0102 1.0000 25.500 0.9648 0.36338 0.36156 -0.1830 0.0180 1.0000 26.000 0.9673 0.37589 0.37407 -0.1869 0.0169 1.0000 26.500 0.9728 0.38542 0.38363 -0.1900 0.0156 1.0000 27.000 0.9807 0.39283 0.39106 -0.1920 0.0150 1.0000 27.500 0.9812 0.40689 0.40513 -0.1964 0.0139 1.0000 28.000 0.9859 0.41644 0.41470 -0.1993 0.0130 1.0000 28.500 0.9917 0.42439 0.42268 -0.2016 0.0125 1.0000 29.000 0.9933 0.43715 0.43545 -0.2052 0.0121 1.0000 29.500 0.9964 0.44817 0.44650 -0.2083 0.0112 1.0000 30.000 0.9997 0.45791 0.45626 -0.2112 0.0108 1.0000 30.500 1.0032 0.46634 0.46471 -0.2136 0.0102 1.0000 31.000 1.0069 0.47536 0.47375 -0.2159 0.0101 1.0000 31.500 1.0070 0.48832 0.48673 -0.2195 0.0099 1.0000 32.000 1.0087 0.49911 0.49755 -0.2224 0.0095 1.0000 32.500 1.0103 0.50917 0.50764 -0.2251 0.0091 1.0000 33.000 1.0115 0.51901 0.51751 -0.2278 0.0089 1.0000 33.500 1.0124 0.52857 0.52710 -0.2305 0.0087 1.0000 34.000 1.0130 0.53791 0.53646 -0.2330 0.0084 1.0000 34.500 1.0133 0.54669 0.54527 -0.2355 0.0082 1.0000 35.000 1.0134 0.55528 0.55389 -0.2379 0.0081 1.0000 36.000 1.0121 0.57394 0.57261 -0.2428 0.0080 1.0000 36.500 1.0107 0.58362 0.58231 -0.2454 0.0080 1.0000 37.000 1.0092 0.59264 0.59137 -0.2479 0.0080 1.0000 37.500 1.0074 0.60216 0.60091 -0.2504 0.0080 1.0000 38.000 1.0052 0.61032 0.60910 -0.2527 0.0080 1.0000 38.500 1.0028 0.61918 0.61799 -0.2551 0.0079 1.0000 39.000 1.0001 0.62759 0.62644 -0.2573 0.0079 1.0000 39.500 0.9971 0.63566 0.63454 -0.2596 0.0079 1.0000 40.000 0.9938 0.64349 0.64240 -0.2618 0.0078 1.0000 40.500 0.9902 0.65122 0.65017 -0.2639 0.0078 1.0000 41.000 0.9865 0.65896 0.65794 -0.2661 0.0076 1.0000 41.500 0.9823 0.66627 0.66529 -0.2681 0.0074 1.0000 42.000 0.9778 0.67336 0.67241 -0.2701 0.0071 1.0000 42.500 0.9730 0.68007 0.67914 -0.2721 0.0068 1.0000 43.000 0.9679 0.68630 0.68540 -0.2740 0.0065 1.0000 43.500 0.9624 0.69187 0.69101 -0.2759 0.0064 1.0000 45.000 0.9452 0.71281 0.71203 -0.2812 0.0060 1.0000 45.500 0.9391 0.71899 0.71823 -0.2828 0.0057 1.0000 46.000 0.9326 0.72451 0.72378 -0.2845 0.0053 1.0000 46.500 0.9258 0.72933 0.72863 -0.2861 0.0050 1.0000 47.000 0.9186 0.73304 0.73238 -0.2877 0.0048 1.0000 47.500 0.9108 0.73577 0.73513 -0.2892 0.0046 1.0000 48.500 0.8962 0.74755 0.74696 -0.2920 0.0045 1.0000 49.000 0.8887 0.75226 0.75169 -0.2932 0.0042 1.0000 49.500 0.8807 0.75560 0.75506 -0.2945 0.0039 1.0000 50.000 0.8723 0.75804 0.75753 -0.2958 0.0036 1.0000 50.500 0.8635 0.75950 0.75901 -0.2970 0.0034 1.0000 51.000 0.8543 0.76025 0.75978 -0.2983 0.0033 1.0000 52.000 0.8367 0.76622 0.76579 -0.3004 0.0031 1.0000 52.500 0.8279 0.76859 0.76818 -0.3013 0.0030 1.0000 53.000 0.8187 0.76980 0.76941 -0.3022 0.0028 1.0000 53.500 0.8092 0.77030 0.76994 -0.3031 0.0026 1.0000 54.000 0.7994 0.76984 0.76949 -0.3040 0.0024 1.0000 54.500 0.7893 0.76873 0.76841 -0.3048 0.0022 1.0000 55.000 0.7789 0.76656 0.76626 -0.3057 0.0021 1.0000 57.000 0.7376 0.76162 0.76138 -0.3081 0.0019 1.0000 57.500 0.7272 0.75987 0.75966 -0.3086 0.0019 1.0000 58.000 0.7164 0.75642 0.75622 -0.3089 0.0018 1.0000 58.500 0.7057 0.75329 0.75311 -0.3093 0.0016 1.0000 59.000 0.6947 0.74932 0.74916 -0.3097 0.0015 1.0000 59.500 0.6835 0.74471 0.74457 -0.3100 0.0013 1.0000 60.000 0.6723 0.73965 0.73953 -0.3103 0.0012 1.0000