XFOIL Version 6.94 Calculated polar for: GOE 803 (HACKLINGER) 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 0.7362 0.01548 0.01002 -0.1579 0.6772 0.0517 0.500 0.7990 0.01392 0.00797 -0.1588 0.6580 0.0615 1.000 0.8585 0.01263 0.00640 -0.1593 0.6367 0.0684 1.500 0.9211 0.01049 0.00364 -0.1592 0.6134 0.0503 2.000 0.9768 0.01020 0.00327 -0.1588 0.5837 0.0612 3.000 1.0837 0.01041 0.00321 -0.1575 0.4877 0.0838 3.500 1.1342 0.01101 0.00349 -0.1563 0.4074 0.0965 4.000 1.1805 0.01074 0.00422 -0.1549 0.3338 1.0000 4.500 1.2309 0.01151 0.00473 -0.1537 0.3004 1.0000 5.000 1.2816 0.01217 0.00524 -0.1527 0.2796 1.0000 5.500 1.3317 0.01283 0.00575 -0.1516 0.2571 1.0000 6.000 1.3823 0.01341 0.00628 -0.1505 0.2405 1.0000 6.500 1.4321 0.01402 0.00684 -0.1494 0.2243 1.0000 7.000 1.4810 0.01466 0.00743 -0.1482 0.2044 1.0000 7.500 1.5293 0.01533 0.00807 -0.1468 0.1870 1.0000 8.000 1.5707 0.01667 0.00902 -0.1447 0.1271 1.0000 8.500 1.6010 0.01908 0.01091 -0.1409 0.0564 1.0000 9.000 1.6359 0.02081 0.01255 -0.1376 0.0377 1.0000 9.500 1.6718 0.02224 0.01403 -0.1345 0.0311 1.0000 10.000 1.7069 0.02354 0.01542 -0.1313 0.0270 1.0000 10.500 1.7387 0.02483 0.01681 -0.1277 0.0186 1.0000 11.000 1.7462 0.02747 0.01939 -0.1206 0.0047 1.0000 11.500 1.7595 0.02995 0.02206 -0.1151 0.0038 1.0000 12.000 1.7718 0.03280 0.02512 -0.1104 0.0035 1.0000 12.500 1.7811 0.03627 0.02884 -0.1065 0.0034 1.0000 13.000 1.7865 0.04048 0.03331 -0.1032 0.0034 1.0000 13.500 1.7873 0.04559 0.03869 -0.1007 0.0033 1.0000 14.000 1.7826 0.05175 0.04513 -0.0990 0.0033 1.0000 14.500 1.7721 0.05902 0.05270 -0.0981 0.0032 1.0000 15.000 1.7554 0.06760 0.06158 -0.0982 0.0032 1.0000 15.500 1.7333 0.07764 0.07193 -0.0995 0.0032 1.0000 16.000 1.7061 0.08926 0.08386 -0.1022 0.0032 1.0000 16.500 1.6753 0.10208 0.09698 -0.1060 0.0032 1.0000 17.000 1.6425 0.11587 0.11108 -0.1110 0.0033 1.0000 17.500 1.6120 0.12965 0.12513 -0.1167 0.0033 1.0000 18.000 1.5846 0.14325 0.13899 -0.1231 0.0033 1.0000 18.500 1.5622 0.15617 0.15214 -0.1298 0.0033 1.0000 19.000 1.5443 0.16855 0.16472 -0.1369 0.0033 1.0000 19.500 1.5302 0.18042 0.17678 -0.1441 0.0033 1.0000 20.000 1.5196 0.19174 0.18828 -0.1514 0.0034 1.0000 20.500 1.5121 0.20262 0.19931 -0.1588 0.0034 1.0000 21.000 1.5073 0.21307 0.20991 -0.1661 0.0034 1.0000 21.500 1.5054 0.22289 0.21986 -0.1732 0.0034 1.0000 22.000 1.5056 0.23223 0.22933 -0.1801 0.0035 1.0000 22.500 1.5073 0.24115 0.23838 -0.1869 0.0035 1.0000 23.000 1.5091 0.25018 0.24755 -0.1940 0.0035 1.0000 23.500 1.5108 0.25942 0.25692 -0.2014 0.0036 1.0000 24.000 1.5116 0.26936 0.26701 -0.2095 0.0036 1.0000 24.500 1.5113 0.28064 0.27846 -0.2184 0.0037 1.0000 25.000 1.4763 0.34324 0.34127 -0.2542 0.0117 1.0000 25.500 1.4892 0.34854 0.34660 -0.2588 0.0114 1.0000 26.000 1.5019 0.35262 0.35072 -0.2617 0.0112 1.0000 26.500 1.5148 0.36263 0.36071 -0.2704 0.0110 1.0000 27.000 1.5289 0.37075 0.36884 -0.2773 0.0101 1.0000 27.500 1.5413 0.37659 0.37470 -0.2827 0.0096 1.0000 28.000 1.5531 0.38181 0.37994 -0.2879 0.0092 1.0000 28.500 1.5639 0.38622 0.38439 -0.2925 0.0090 1.0000 29.000 1.5741 0.39030 0.38851 -0.2952 0.0088 1.0000 29.500 1.5864 0.39771 0.39593 -0.3034 0.0088 1.0000 30.000 1.5999 0.40535 0.40358 -0.3106 0.0084 1.0000 30.500 1.6111 0.41094 0.40920 -0.3164 0.0079 1.0000 31.000 1.6215 0.41603 0.41432 -0.3219 0.0076 1.0000 31.500 1.6309 0.42058 0.41890 -0.3273 0.0072 1.0000 32.000 1.6391 0.42436 0.42272 -0.3322 0.0070 1.0000 32.500 1.6458 0.42787 0.42629 -0.3356 0.0068 1.0000 33.000 1.6583 0.43451 0.43292 -0.3439 0.0067 1.0000 33.500 1.6698 0.44024 0.43868 -0.3503 0.0059 1.0000 34.000 1.6776 0.44370 0.44218 -0.3558 0.0054 1.0000 34.500 1.6836 0.44607 0.44459 -0.3609 0.0052 1.0000 35.000 1.6895 0.44924 0.44779 -0.3657 0.0051 1.0000 35.500 1.7034 0.45599 0.45455 -0.3735 0.0045 1.0000 36.000 1.7103 0.45932 0.45791 -0.3792 0.0040 1.0000 37.000 0.9632 0.49706 0.49599 -0.2100 0.0037 1.0000 37.500 0.9601 0.50389 0.50284 -0.2118 0.0036 1.0000 38.000 0.9581 0.51342 0.51240 -0.2137 0.0033 1.0000 38.500 0.9551 0.52059 0.51960 -0.2155 0.0029 1.0000 39.000 0.9517 0.52693 0.52597 -0.2174 0.0026 1.0000 39.500 0.9475 0.53215 0.53122 -0.2193 0.0024 1.0000 40.000 0.9436 0.53953 0.53862 -0.2210 0.0024 1.0000 40.500 0.9404 0.54797 0.54708 -0.2228 0.0023 1.0000 41.000 0.9367 0.55516 0.55430 -0.2244 0.0021 1.0000 41.500 0.9324 0.56150 0.56067 -0.2262 0.0018 1.0000 42.000 0.9277 0.56728 0.56648 -0.2279 0.0016 1.0000 42.500 0.9225 0.57235 0.57158 -0.2297 0.0015 1.0000 43.500 0.9119 0.58471 0.58399 -0.2331 0.0014 1.0000 44.000 0.9074 0.59186 0.59116 -0.2346 0.0013 1.0000 44.500 0.9023 0.59797 0.59730 -0.2361 0.0012 1.0000 45.000 0.8966 0.60344 0.60280 -0.2377 0.0010 1.0000 45.500 0.8906 0.60851 0.60789 -0.2393 0.0009 1.0000 46.000 0.8842 0.61302 0.61243 -0.2409 0.0008 1.0000 46.500 0.8773 0.61676 0.61620 -0.2426 0.0007 1.0000 47.000 0.8696 0.61983 0.61931 -0.2442 0.0006 1.0000 47.500 0.8641 0.62682 0.62631 -0.2456 0.0006 1.0000 48.000 0.8578 0.63193 0.63144 -0.2469 0.0004 1.0000 48.500 0.8506 0.63563 0.63517 -0.2484 0.0003 1.0000 49.500 0.8358 0.64329 0.64287 -0.2512 0.0003 1.0000 50.000 0.8284 0.64721 0.64681 -0.2525 0.0003 1.0000 50.500 0.8208 0.65056 0.65019 -0.2538 0.0002 1.0000 51.000 0.8127 0.65315 0.65281 -0.2552 0.0001 1.0000 51.500 0.8040 0.65485 0.65453 -0.2567 0.0000 1.0000 52.500 0.7876 0.66041 0.66013 -0.2592 0.0000 1.0000 53.000 0.7792 0.66282 0.66257 -0.2603 0.0000 1.0000 53.500 0.7706 0.66491 0.66467 -0.2615 0.0000 1.0000 54.000 0.7618 0.66663 0.66642 -0.2627 0.0000 1.0000 54.500 0.7528 0.66791 0.66772 -0.2639 0.0000 1.0000 55.000 0.7436 0.66887 0.66870 -0.2650 0.0001 1.0000 55.500 0.7341 0.66931 0.66916 -0.2662 0.0002 1.0000 56.000 0.7245 0.66938 0.66926 -0.2673 0.0003 1.0000 56.500 0.7146 0.66900 0.66890 -0.2685 0.0004 1.0000 57.000 0.7046 0.66830 0.66822 -0.2696 0.0005 1.0000 57.500 0.6943 0.66710 0.66705 -0.2707 0.0005 1.0000 58.000 0.6836 0.66533 0.66530 -0.2719 0.0006 1.0000 60.000 0.6429 0.66144 0.66148 -0.2757 0.0006 1.0000