XFOIL Version 6.94 Calculated polar for: GOE 593 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 ------- -------- --------- --------- -------- ------- ------- 0.500 0.6571 0.00884 0.00363 -0.1201 0.7143 1.0000 1.000 0.6957 0.00894 0.00357 -0.1166 0.6920 1.0000 1.500 0.7342 0.00907 0.00356 -0.1130 0.6681 1.0000 2.000 0.7722 0.00924 0.00359 -0.1092 0.6420 1.0000 2.500 0.8099 0.00945 0.00368 -0.1054 0.6145 1.0000 3.000 0.8465 0.00974 0.00384 -0.1013 0.5836 1.0000 3.500 0.8811 0.01006 0.00404 -0.0967 0.5464 1.0000 4.000 0.9011 0.01070 0.00424 -0.0893 0.4714 1.0000 4.500 0.9250 0.01145 0.00462 -0.0829 0.4111 1.0000 5.000 0.9456 0.01236 0.00513 -0.0760 0.3468 1.0000 5.500 0.9774 0.01296 0.00561 -0.0714 0.3199 1.0000 6.000 1.0004 0.01372 0.00615 -0.0652 0.2790 1.0000 6.500 1.0280 0.01447 0.00674 -0.0600 0.2484 1.0000 7.000 1.0550 0.01535 0.00743 -0.0550 0.2116 1.0000 7.500 1.0653 0.01721 0.00869 -0.0478 0.1156 1.0000 8.000 1.0735 0.01945 0.01050 -0.0409 0.0465 1.0000 8.500 1.0892 0.02139 0.01224 -0.0354 0.0069 1.0000 9.000 1.1149 0.02283 0.01377 -0.0315 0.0040 1.0000 9.500 1.1407 0.02433 0.01542 -0.0280 0.0038 1.0000 10.000 1.1639 0.02610 0.01736 -0.0245 0.0037 1.0000 10.500 1.1841 0.02819 0.01964 -0.0211 0.0038 1.0000 11.000 1.2010 0.03067 0.02232 -0.0179 0.0038 1.0000 12.500 1.2358 0.04064 0.03295 -0.0105 0.0041 1.0000 13.000 1.2405 0.04514 0.03769 -0.0089 0.0042 1.0000 13.500 1.2409 0.05043 0.04325 -0.0080 0.0044 1.0000 14.000 1.2366 0.05666 0.04973 -0.0078 0.0046 1.0000 14.500 1.2276 0.06390 0.05723 -0.0085 0.0047 1.0000 15.000 1.2133 0.07236 0.06595 -0.0101 0.0048 1.0000 15.500 1.1951 0.08184 0.07568 -0.0126 0.0049 1.0000 16.000 1.1779 0.09153 0.08560 -0.0155 0.0049 1.0000 16.500 1.1597 0.10156 0.09582 -0.0187 0.0050 1.0000 17.000 1.1470 0.11086 0.10528 -0.0218 0.0051 1.0000 17.500 1.1428 0.11897 0.11358 -0.0247 0.0053 1.0000 18.000 1.1408 0.12668 0.12146 -0.0276 0.0056 1.0000 18.500 1.1412 0.13377 0.12869 -0.0301 0.0059 1.0000 19.000 1.1474 0.13938 0.13439 -0.0318 0.0063 1.0000 19.500 1.1669 0.14166 0.13666 -0.0311 0.0067 1.0000 20.000 1.1634 0.15048 0.14577 -0.0358 0.0069 1.0000 20.500 1.1582 0.15965 0.15532 -0.0406 0.0076 1.0000 21.000 1.1503 0.16928 0.16523 -0.0460 0.0078 1.0000 21.500 1.1408 0.17942 0.17562 -0.0519 0.0082 1.0000 22.000 1.1315 0.19016 0.18658 -0.0586 0.0086 1.0000 22.500 1.1058 0.20670 0.20342 -0.0696 0.0085 1.0000 24.500 0.8235 0.30041 0.29820 -0.1184 0.0188 1.0000 25.000 0.8283 0.31079 0.30859 -0.1226 0.0181 1.0000 25.500 0.8351 0.31985 0.31768 -0.1263 0.0164 1.0000 26.000 0.8449 0.32688 0.32474 -0.1290 0.0156 1.0000 26.500 0.8478 0.33837 0.33625 -0.1336 0.0143 1.0000 27.000 0.8550 0.34637 0.34428 -0.1370 0.0132 1.0000 27.500 0.8607 0.35596 0.35389 -0.1405 0.0127 1.0000 28.000 0.8660 0.36570 0.36366 -0.1442 0.0114 1.0000 28.500 0.8724 0.37354 0.37153 -0.1473 0.0107 1.0000 29.000 0.8769 0.38361 0.38163 -0.1509 0.0103 1.0000 29.500 0.8815 0.39344 0.39148 -0.1545 0.0094 1.0000 30.000 0.8864 0.40197 0.40004 -0.1578 0.0088 1.0000 30.500 0.8921 0.40939 0.40751 -0.1605 0.0084 1.0000 31.000 0.8945 0.42086 0.41900 -0.1644 0.0082 1.0000 31.500 0.8982 0.43059 0.42876 -0.1677 0.0076 1.0000 32.000 0.9016 0.43963 0.43782 -0.1709 0.0072 1.0000 32.500 0.9047 0.44810 0.44633 -0.1741 0.0069 1.0000 33.000 0.9076 0.45595 0.45422 -0.1770 0.0067 1.0000 33.500 0.9096 0.46600 0.46429 -0.1803 0.0066 1.0000 34.000 0.9115 0.47541 0.47374 -0.1835 0.0065 1.0000 34.500 0.9133 0.48494 0.48330 -0.1866 0.0064 1.0000 35.000 0.9146 0.49381 0.49220 -0.1896 0.0062 1.0000 35.500 0.9158 0.50287 0.50130 -0.1926 0.0059 1.0000 36.000 0.9164 0.51134 0.50980 -0.1956 0.0059 1.0000 36.500 0.9168 0.51988 0.51838 -0.1985 0.0057 1.0000 37.000 0.9167 0.52806 0.52660 -0.2014 0.0056 1.0000 37.500 0.9163 0.53619 0.53476 -0.2043 0.0056 1.0000 38.000 0.9156 0.54416 0.54277 -0.2071 0.0055 1.0000 38.500 0.9146 0.55194 0.55059 -0.2099 0.0054 1.0000 39.000 0.9132 0.55954 0.55822 -0.2126 0.0053 1.0000 39.500 0.9114 0.56693 0.56565 -0.2153 0.0052 1.0000 40.000 0.9093 0.57406 0.57281 -0.2180 0.0052 1.0000 40.500 0.9069 0.58116 0.57995 -0.2207 0.0051 1.0000 41.000 0.9040 0.58781 0.58663 -0.2232 0.0051 1.0000 42.500 0.8943 0.60924 0.60815 -0.2307 0.0050 1.0000 43.000 0.8906 0.61615 0.61510 -0.2331 0.0050 1.0000 43.500 0.8870 0.62342 0.62240 -0.2353 0.0048 1.0000 44.000 0.8828 0.62994 0.62895 -0.2376 0.0045 1.0000 44.500 0.8783 0.63603 0.63508 -0.2398 0.0042 1.0000 45.000 0.8733 0.64146 0.64054 -0.2420 0.0040 1.0000 45.500 0.8680 0.64655 0.64566 -0.2442 0.0038 1.0000 46.000 0.8619 0.65067 0.64981 -0.2463 0.0037 1.0000 47.000 0.8509 0.66269 0.66188 -0.2502 0.0036 1.0000 47.500 0.8452 0.66805 0.66726 -0.2520 0.0035 1.0000 48.000 0.8389 0.67268 0.67192 -0.2539 0.0032 1.0000 48.500 0.8323 0.67671 0.67598 -0.2557 0.0029 1.0000 49.000 0.8253 0.67994 0.67923 -0.2574 0.0028 1.0000 49.500 0.8178 0.68219 0.68152 -0.2593 0.0026 1.0000 50.000 0.8097 0.68406 0.68342 -0.2610 0.0025 1.0000 51.000 0.7952 0.69158 0.69097 -0.2640 0.0025 1.0000 51.500 0.7878 0.69475 0.69417 -0.2654 0.0024 1.0000 52.000 0.7799 0.69680 0.69624 -0.2668 0.0022 1.0000 52.500 0.7716 0.69836 0.69783 -0.2681 0.0020 1.0000 53.000 0.7630 0.69910 0.69860 -0.2695 0.0019 1.0000 53.500 0.7542 0.69936 0.69887 -0.2708 0.0017 1.0000 54.000 0.7450 0.69888 0.69842 -0.2720 0.0016 1.0000 54.500 0.7354 0.69779 0.69735 -0.2734 0.0016 1.0000 56.000 0.7073 0.69653 0.69614 -0.2764 0.0015 1.0000 56.500 0.6978 0.69535 0.69498 -0.2773 0.0015 1.0000 57.000 0.6882 0.69389 0.69354 -0.2781 0.0014 1.0000 57.500 0.6783 0.69147 0.69114 -0.2789 0.0014 1.0000 58.000 0.6683 0.68892 0.68861 -0.2796 0.0014 1.0000 58.500 0.6581 0.68574 0.68545 -0.2803 0.0013 1.0000 59.000 0.6477 0.68211 0.68183 -0.2809 0.0012 1.0000 59.500 0.6371 0.67785 0.67759 -0.2815 0.0011 1.0000 60.000 0.6265 0.67344 0.67320 -0.2821 0.0010 1.0000