XFOIL Version 6.94 Calculated polar for: GOE 436 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 0.4071 0.01045 0.00296 -0.0776 0.6832 0.1272 0.500 0.4362 0.00861 0.00283 -0.0725 0.6404 0.6951 1.000 0.5792 0.00873 0.00304 -0.0900 0.5700 1.0000 1.500 0.6180 0.00915 0.00309 -0.0864 0.5165 1.0000 2.000 0.6581 0.00963 0.00324 -0.0831 0.4786 1.0000 2.500 0.7011 0.01011 0.00352 -0.0804 0.4536 1.0000 3.000 0.7453 0.01064 0.00384 -0.0780 0.4345 1.0000 3.500 0.7898 0.01107 0.00416 -0.0757 0.4142 1.0000 4.000 0.8315 0.01144 0.00438 -0.0728 0.3825 1.0000 4.500 0.8719 0.01183 0.00455 -0.0698 0.3444 1.0000 5.000 0.9156 0.01224 0.00486 -0.0674 0.3213 1.0000 5.500 0.9562 0.01277 0.00518 -0.0645 0.2780 1.0000 6.000 0.9970 0.01339 0.00564 -0.0618 0.2373 1.0000 6.500 1.0165 0.01546 0.00688 -0.0560 0.1125 1.0000 7.000 1.0410 0.01713 0.00820 -0.0509 0.0476 1.0000 7.500 1.0634 0.01860 0.00947 -0.0453 0.0060 1.0000 8.000 1.0929 0.01955 0.01050 -0.0408 0.0050 1.0000 8.500 1.1213 0.02060 0.01170 -0.0365 0.0047 1.0000 9.000 1.1471 0.02186 0.01312 -0.0320 0.0047 1.0000 9.500 1.1696 0.02337 0.01481 -0.0275 0.0047 1.0000 10.000 1.1887 0.02519 0.01682 -0.0232 0.0047 1.0000 10.500 1.2044 0.02739 0.01921 -0.0190 0.0048 1.0000 11.000 1.2170 0.03003 0.02206 -0.0153 0.0049 1.0000 11.500 1.2260 0.03324 0.02549 -0.0122 0.0050 1.0000 12.000 1.2311 0.03717 0.02965 -0.0098 0.0051 1.0000 12.500 1.2308 0.04212 0.03484 -0.0084 0.0053 1.0000 13.000 1.2259 0.04814 0.04112 -0.0081 0.0054 1.0000 13.500 1.2154 0.05543 0.04865 -0.0089 0.0055 1.0000 14.000 1.2024 0.06361 0.05707 -0.0106 0.0056 1.0000 14.500 1.1880 0.07242 0.06609 -0.0130 0.0057 1.0000 15.000 1.1729 0.08154 0.07539 -0.0156 0.0059 1.0000 15.500 1.1624 0.09005 0.08403 -0.0180 0.0060 1.0000 16.000 1.1586 0.09739 0.09145 -0.0198 0.0061 1.0000 16.500 1.1616 0.10404 0.09823 -0.0216 0.0063 1.0000 17.000 1.1642 0.11119 0.10560 -0.0241 0.0066 1.0000 17.500 1.1710 0.11728 0.11190 -0.0257 0.0071 1.0000 18.000 1.1791 0.12290 0.11767 -0.0269 0.0075 1.0000 18.500 1.2013 0.12521 0.12002 -0.0252 0.0080 1.0000 19.000 1.1886 0.13628 0.13147 -0.0318 0.0083 1.0000 19.500 1.1692 0.14900 0.14467 -0.0391 0.0088 1.0000 20.000 1.1487 0.16224 0.15828 -0.0469 0.0091 1.0000 20.500 1.1264 0.17657 0.17293 -0.0559 0.0093 1.0000 21.000 1.0960 0.19428 0.19096 -0.0671 0.0094 1.0000 22.000 0.8251 0.26400 0.26168 -0.1066 0.0241 1.0000 22.500 0.8205 0.27700 0.27468 -0.1134 0.0223 1.0000 23.000 0.8294 0.28497 0.28268 -0.1168 0.0212 1.0000 23.500 0.8430 0.29189 0.28963 -0.1189 0.0207 1.0000 24.000 0.8424 0.30372 0.30147 -0.1247 0.0187 1.0000 24.500 0.8521 0.31106 0.30884 -0.1277 0.0178 1.0000 25.000 0.8565 0.32195 0.31974 -0.1321 0.0166 1.0000 25.500 0.8638 0.33030 0.32812 -0.1355 0.0154 1.0000 26.000 0.8747 0.33733 0.33519 -0.1377 0.0148 1.0000 26.500 0.8763 0.34935 0.34721 -0.1428 0.0136 1.0000 27.000 0.8829 0.35781 0.35571 -0.1462 0.0128 1.0000 27.500 0.8914 0.36512 0.36306 -0.1488 0.0122 1.0000 28.000 0.8941 0.37703 0.37498 -0.1532 0.0116 1.0000 28.500 0.8995 0.38629 0.38428 -0.1567 0.0108 1.0000 29.000 0.9049 0.39474 0.39276 -0.1599 0.0102 1.0000 30.000 0.9141 0.41327 0.41135 -0.1666 0.0099 1.0000 30.500 0.9178 0.42367 0.42177 -0.1701 0.0094 1.0000 31.000 0.9217 0.43297 0.43111 -0.1734 0.0091 1.0000 31.500 0.9253 0.44215 0.44032 -0.1766 0.0087 1.0000 32.000 0.9285 0.45104 0.44924 -0.1798 0.0083 1.0000 32.500 0.9314 0.45953 0.45777 -0.1829 0.0081 1.0000 33.000 0.9344 0.46774 0.46601 -0.1857 0.0080 1.0000 33.500 0.9361 0.47746 0.47577 -0.1891 0.0079 1.0000 34.000 0.9377 0.48689 0.48523 -0.1923 0.0079 1.0000 34.500 0.9390 0.49628 0.49466 -0.1955 0.0079 1.0000 35.000 0.9401 0.50539 0.50380 -0.1986 0.0079 1.0000 35.500 0.9409 0.51471 0.51316 -0.2016 0.0078 1.0000 36.000 0.9413 0.52329 0.52177 -0.2046 0.0078 1.0000 36.500 0.9415 0.53198 0.53050 -0.2076 0.0077 1.0000 37.000 0.9413 0.54068 0.53924 -0.2105 0.0076 1.0000 37.500 0.9407 0.54903 0.54763 -0.2134 0.0076 1.0000 38.000 0.9399 0.55738 0.55601 -0.2162 0.0075 1.0000 38.500 0.9386 0.56559 0.56426 -0.2190 0.0074 1.0000 39.000 0.9372 0.57373 0.57244 -0.2218 0.0073 1.0000 39.500 0.9353 0.58170 0.58045 -0.2245 0.0070 1.0000 40.000 0.9331 0.58949 0.58828 -0.2272 0.0068 1.0000 40.500 0.9307 0.59709 0.59592 -0.2298 0.0065 1.0000 41.000 0.9276 0.60397 0.60283 -0.2324 0.0063 1.0000 42.000 0.9208 0.61943 0.61835 -0.2374 0.0061 1.0000 42.500 0.9178 0.62839 0.62734 -0.2398 0.0060 1.0000 43.000 0.9142 0.63623 0.63522 -0.2422 0.0056 1.0000 43.500 0.9100 0.64326 0.64228 -0.2445 0.0052 1.0000 44.000 0.9054 0.64963 0.64868 -0.2469 0.0050 1.0000 44.500 0.9003 0.65548 0.65456 -0.2492 0.0047 1.0000 45.500 0.8899 0.66930 0.66844 -0.2535 0.0045 1.0000 46.000 0.8851 0.67679 0.67597 -0.2555 0.0043 1.0000 46.500 0.8795 0.68295 0.68215 -0.2575 0.0040 1.0000 47.000 0.8734 0.68827 0.68750 -0.2595 0.0037 1.0000 47.500 0.8669 0.69293 0.69220 -0.2615 0.0035 1.0000 48.000 0.8597 0.69646 0.69575 -0.2635 0.0032 1.0000 49.000 0.8463 0.70758 0.70692 -0.2671 0.0031 1.0000 49.500 0.8396 0.71282 0.71219 -0.2687 0.0031 1.0000 50.000 0.8324 0.71709 0.71648 -0.2703 0.0028 1.0000 50.500 0.8248 0.72084 0.72026 -0.2719 0.0025 1.0000 51.000 0.8168 0.72341 0.72286 -0.2735 0.0023 1.0000 51.500 0.8084 0.72543 0.72491 -0.2752 0.0021 1.0000 52.000 0.7995 0.72666 0.72617 -0.2768 0.0020 1.0000 53.500 0.7742 0.73455 0.73412 -0.2807 0.0019 1.0000 54.000 0.7654 0.73619 0.73579 -0.2819 0.0019 1.0000 54.500 0.7564 0.73712 0.73673 -0.2830 0.0018 1.0000 55.000 0.7471 0.73745 0.73709 -0.2841 0.0017 1.0000 55.500 0.7376 0.73739 0.73705 -0.2853 0.0015 1.0000 56.000 0.7278 0.73673 0.73642 -0.2863 0.0013 1.0000 56.500 0.7179 0.73538 0.73508 -0.2873 0.0012 1.0000 57.000 0.7077 0.73345 0.73318 -0.2883 0.0011 1.0000 57.500 0.6971 0.73088 0.73063 -0.2893 0.0010 1.0000 58.000 0.6861 0.72748 0.72724 -0.2903 0.0009 1.0000 59.000 0.6663 0.72531 0.72511 -0.2915 0.0009 1.0000 59.500 0.6559 0.72232 0.72213 -0.2921 0.0008 1.0000 60.000 0.6452 0.71870 0.71853 -0.2926 0.0006 1.0000