XFOIL Version 6.94 Calculated polar for: GOE 480 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.5742 0.01063 0.00332 -0.1155 0.6468 0.0725 0.500 0.6262 0.01038 0.00310 -0.1145 0.6311 0.0768 1.000 0.6778 0.01020 0.00292 -0.1134 0.6148 0.0842 1.500 0.7285 0.01005 0.00281 -0.1122 0.5969 0.1107 2.000 0.7735 0.00923 0.00300 -0.1103 0.5784 0.4849 3.500 0.9398 0.00959 0.00356 -0.1105 0.4359 1.0000 4.000 0.9783 0.01023 0.00392 -0.1070 0.3855 1.0000 4.500 1.0022 0.01155 0.00460 -0.1013 0.2877 1.0000 5.000 1.0291 0.01276 0.00538 -0.0961 0.2173 1.0000 5.500 1.0130 0.01556 0.00725 -0.0837 0.0529 1.0000 6.000 1.0347 0.01683 0.00834 -0.0780 0.0055 1.0000 6.500 1.0683 0.01763 0.00916 -0.0744 0.0052 1.0000 7.000 1.1009 0.01853 0.01010 -0.0709 0.0053 1.0000 7.500 1.1317 0.01959 0.01124 -0.0673 0.0056 1.0000 8.000 1.1600 0.02087 0.01262 -0.0637 0.0059 1.0000 8.500 1.1880 0.02228 0.01412 -0.0603 0.0066 1.0000 9.000 1.2132 0.02398 0.01594 -0.0570 0.0073 1.0000 9.500 1.2354 0.02604 0.01814 -0.0537 0.0079 1.0000 10.000 1.2591 0.02813 0.02036 -0.0510 0.0089 1.0000 10.500 1.2780 0.03075 0.02314 -0.0482 0.0099 1.0000 11.000 1.2981 0.03342 0.02596 -0.0458 0.0111 1.0000 11.500 1.3129 0.03670 0.02941 -0.0434 0.0121 1.0000 12.000 1.3239 0.04049 0.03337 -0.0413 0.0131 1.0000 12.500 1.3202 0.04601 0.03906 -0.0393 0.0138 1.0000 13.000 1.3332 0.05010 0.04334 -0.0380 0.0153 1.0000 13.500 1.3234 0.05695 0.05036 -0.0370 0.0161 1.0000 14.000 1.3297 0.06226 0.05587 -0.0364 0.0174 1.0000 14.500 1.3198 0.06955 0.06332 -0.0360 0.0188 1.0000 15.000 1.3196 0.07554 0.06940 -0.0353 0.0192 1.0000 15.500 1.3284 0.08053 0.07456 -0.0346 0.0198 1.0000 16.000 1.3463 0.08366 0.07783 -0.0322 0.0208 1.0000 16.500 1.3746 0.08540 0.07968 -0.0289 0.0209 1.0000 17.000 1.4291 0.08448 0.07863 -0.0239 0.0189 1.0000 17.500 1.4178 0.09255 0.08710 -0.0255 0.0187 1.0000 18.000 1.4074 0.10099 0.09592 -0.0276 0.0184 1.0000 18.500 1.3848 0.11145 0.10677 -0.0318 0.0177 1.0000 19.000 1.3872 0.11815 0.11355 -0.0334 0.0160 1.0000 19.500 1.3596 0.13012 0.12591 -0.0395 0.0159 1.0000 20.000 1.3368 0.14181 0.13793 -0.0457 0.0160 1.0000 20.500 1.3077 0.15527 0.15173 -0.0538 0.0160 1.0000 21.000 1.2928 0.16625 0.16293 -0.0600 0.0162 1.0000 21.500 0.8738 0.26570 0.26388 -0.1250 0.0310 1.0000 22.000 0.8799 0.27453 0.27271 -0.1288 0.0270 1.0000 22.500 0.8865 0.28302 0.28122 -0.1324 0.0232 1.0000 23.000 0.8927 0.29177 0.28999 -0.1360 0.0200 1.0000 23.500 0.8983 0.30116 0.29939 -0.1397 0.0174 1.0000 24.000 0.9041 0.31025 0.30849 -0.1433 0.0150 1.0000 25.000 0.9173 0.32713 0.32540 -0.1499 0.0119 1.0000 25.500 0.9205 0.33873 0.33701 -0.1539 0.0105 1.0000 26.000 0.9280 0.34563 0.34394 -0.1567 0.0097 1.0000 26.500 0.9307 0.35833 0.35664 -0.1607 0.0087 1.0000 27.000 0.9361 0.36709 0.36543 -0.1639 0.0080 1.0000 27.500 0.9438 0.37279 0.37116 -0.1662 0.0076 1.0000 28.000 0.9446 0.38794 0.38631 -0.1706 0.0070 1.0000 28.500 0.9488 0.39778 0.39617 -0.1738 0.0065 1.0000 29.000 0.9531 0.40679 0.40520 -0.1769 0.0062 1.0000 29.500 0.9574 0.41460 0.41304 -0.1797 0.0059 1.0000 30.000 0.9616 0.42320 0.42166 -0.1824 0.0058 1.0000 30.500 0.9631 0.43567 0.43414 -0.1861 0.0057 1.0000 31.000 0.9658 0.44655 0.44505 -0.1893 0.0055 1.0000 31.500 0.9684 0.45673 0.45525 -0.1923 0.0054 1.0000 32.000 0.9706 0.46648 0.46503 -0.1953 0.0051 1.0000 32.500 0.9725 0.47600 0.47458 -0.1982 0.0051 1.0000 33.000 0.9741 0.48570 0.48430 -0.2011 0.0049 1.0000 33.500 0.9754 0.49502 0.49365 -0.2040 0.0049 1.0000 34.000 0.9763 0.50420 0.50285 -0.2068 0.0048 1.0000 34.500 0.9769 0.51341 0.51209 -0.2097 0.0048 1.0000 35.000 0.9772 0.52244 0.52115 -0.2124 0.0048 1.0000 35.500 0.9772 0.53138 0.53012 -0.2152 0.0046 1.0000 36.000 0.9768 0.54032 0.53909 -0.2179 0.0048 1.0000 36.500 0.9761 0.54898 0.54777 -0.2206 0.0047 1.0000 37.000 0.9750 0.55754 0.55636 -0.2232 0.0047 1.0000 37.500 0.9736 0.56601 0.56486 -0.2258 0.0047 1.0000 38.000 0.9719 0.57422 0.57310 -0.2284 0.0049 1.0000 38.500 0.9699 0.58235 0.58126 -0.2310 0.0049 1.0000 39.000 0.9676 0.59028 0.58922 -0.2335 0.0049 1.0000 39.500 0.9649 0.59776 0.59674 -0.2360 0.0051 1.0000 40.000 0.9619 0.60521 0.60421 -0.2385 0.0051 1.0000 40.500 0.9586 0.61237 0.61140 -0.2409 0.0052 1.0000 41.000 0.9550 0.61943 0.61849 -0.2433 0.0052 1.0000 41.500 0.9510 0.62602 0.62512 -0.2456 0.0054 1.0000 42.000 0.9468 0.63260 0.63173 -0.2479 0.0054 1.0000 42.500 0.9424 0.63907 0.63823 -0.2502 0.0053 1.0000 43.000 0.9377 0.64548 0.64467 -0.2524 0.0053 1.0000 43.500 0.9326 0.65155 0.65077 -0.2545 0.0051 1.0000 44.000 0.9274 0.65768 0.65693 -0.2566 0.0048 1.0000 44.500 0.9219 0.66327 0.66255 -0.2587 0.0046 1.0000 45.000 0.9159 0.66824 0.66755 -0.2608 0.0044 1.0000 45.500 0.9095 0.67261 0.67195 -0.2628 0.0043 1.0000 46.500 0.8965 0.68433 0.68372 -0.2665 0.0041 1.0000 47.000 0.8903 0.69095 0.69036 -0.2682 0.0041 1.0000 47.500 0.8840 0.69713 0.69657 -0.2699 0.0039 1.0000 48.000 0.8772 0.70246 0.70193 -0.2715 0.0035 1.0000 48.500 0.8698 0.70628 0.70577 -0.2732 0.0031 1.0000 49.000 0.8619 0.70921 0.70873 -0.2749 0.0029 1.0000 49.500 0.8534 0.71073 0.71028 -0.2766 0.0027 1.0000 50.500 0.8372 0.71938 0.71897 -0.2794 0.0026 1.0000 51.000 0.8298 0.72501 0.72461 -0.2806 0.0026 1.0000 51.500 0.8219 0.72908 0.72871 -0.2818 0.0025 1.0000 52.000 0.8134 0.73171 0.73136 -0.2830 0.0022 1.0000 52.500 0.8046 0.73370 0.73337 -0.2842 0.0018 1.0000 53.000 0.7953 0.73450 0.73419 -0.2855 0.0016 1.0000 53.500 0.7857 0.73439 0.73411 -0.2867 0.0014 1.0000 54.000 0.7755 0.73335 0.73309 -0.2880 0.0013 1.0000 55.000 0.7577 0.73920 0.73897 -0.2896 0.0011 1.0000 55.500 0.7482 0.73962 0.73941 -0.2904 0.0009 1.0000 56.000 0.7381 0.73868 0.73849 -0.2913 0.0008 1.0000 56.500 0.7273 0.73596 0.73578 -0.2923 0.0006 1.0000 57.500 0.7076 0.73651 0.73636 -0.2935 0.0006 1.0000 58.000 0.6974 0.73514 0.73501 -0.2941 0.0005 1.0000 58.500 0.6870 0.73329 0.73317 -0.2947 0.0004 1.0000 59.000 0.6762 0.73040 0.73030 -0.2952 0.0002 1.0000 59.500 0.6650 0.72579 0.72570 -0.2958 0.0000 1.0000