XFOIL Version 6.94 Calculated polar for: GOE 418 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 0.5087 0.01150 0.00396 -0.0953 0.5621 0.1259 0.500 0.5626 0.01131 0.00382 -0.0942 0.5492 0.1317 1.000 0.6154 0.01119 0.00365 -0.0931 0.5363 0.1374 1.500 0.6688 0.01102 0.00358 -0.0921 0.5233 0.1438 2.000 0.7209 0.01097 0.00351 -0.0908 0.5077 0.1506 2.500 0.7721 0.01095 0.00348 -0.0894 0.4893 0.1604 3.000 0.8239 0.01090 0.00355 -0.0881 0.4716 0.1833 3.500 0.8635 0.00981 0.00386 -0.0849 0.4528 0.7034 5.500 1.0858 0.01117 0.00510 -0.0839 0.3443 1.0000 6.000 1.1286 0.01175 0.00556 -0.0812 0.3206 1.0000 6.500 1.1674 0.01247 0.00611 -0.0779 0.2893 1.0000 7.000 1.1971 0.01356 0.00686 -0.0732 0.2287 1.0000 7.500 1.2065 0.01528 0.00808 -0.0653 0.1596 1.0000 8.000 1.2282 0.01645 0.00913 -0.0596 0.1434 1.0000 8.500 1.2550 0.01748 0.01015 -0.0550 0.1358 1.0000 9.000 1.2814 0.01862 0.01132 -0.0507 0.1315 1.0000 9.500 1.3048 0.02001 0.01270 -0.0465 0.1236 1.0000 10.000 1.3288 0.02151 0.01423 -0.0428 0.1179 1.0000 10.500 1.3492 0.02338 0.01613 -0.0391 0.1136 1.0000 11.000 1.3771 0.02494 0.01778 -0.0366 0.1090 1.0000 11.500 1.3969 0.02720 0.02008 -0.0338 0.1050 1.0000 12.000 1.4175 0.02959 0.02258 -0.0316 0.1017 1.0000 12.500 1.4402 0.03199 0.02502 -0.0299 0.0940 1.0000 13.000 1.4626 0.03455 0.02768 -0.0284 0.0871 1.0000 13.500 1.4752 0.03813 0.03119 -0.0271 0.0671 1.0000 14.000 1.4613 0.04454 0.03747 -0.0259 0.0449 1.0000 14.500 1.4576 0.05025 0.04326 -0.0252 0.0386 1.0000 15.000 1.4554 0.05599 0.04911 -0.0250 0.0350 1.0000 15.500 1.4544 0.06181 0.05506 -0.0250 0.0325 1.0000 16.000 1.4519 0.06801 0.06140 -0.0254 0.0312 1.0000 16.500 1.4479 0.07460 0.06813 -0.0262 0.0289 1.0000 17.000 1.4385 0.08214 0.07580 -0.0276 0.0268 1.0000 17.500 1.4342 0.08925 0.08308 -0.0291 0.0265 1.0000 18.000 1.4279 0.09684 0.09085 -0.0311 0.0251 1.0000 18.500 1.4176 0.10526 0.09943 -0.0338 0.0237 1.0000 19.000 1.4067 0.11401 0.10835 -0.0370 0.0227 1.0000 19.500 1.3989 0.12242 0.11694 -0.0403 0.0217 1.0000 20.000 1.3893 0.13130 0.12600 -0.0443 0.0211 1.0000 20.500 1.3779 0.14062 0.13548 -0.0488 0.0199 1.0000 21.000 1.3664 0.15011 0.14515 -0.0538 0.0195 1.0000 21.500 1.3566 0.15941 0.15463 -0.0589 0.0187 1.0000 22.000 1.3421 0.16976 0.16512 -0.0650 0.0159 1.0000 22.500 1.3301 0.17967 0.17522 -0.0712 0.0157 1.0000 23.000 1.3191 0.18951 0.18521 -0.0774 0.0144 1.0000 23.500 1.2873 0.20411 0.19981 -0.0871 0.0050 1.0000 24.000 1.2826 0.21282 0.20863 -0.0930 0.0042 1.0000 24.500 1.2735 0.22264 0.21854 -0.0998 0.0027 1.0000 25.000 1.2707 0.23099 0.22699 -0.1057 0.0024 1.0000 25.500 1.2680 0.23932 0.23545 -0.1117 0.0022 1.0000 26.000 1.2661 0.24750 0.24375 -0.1176 0.0021 1.0000 26.500 1.2597 0.25717 0.25358 -0.1245 0.0020 1.0000 27.000 1.2506 0.26798 0.26457 -0.1320 0.0020 1.0000 27.500 1.2340 0.28224 0.27905 -0.1412 0.0021 1.0000 28.000 1.2278 0.29387 0.29081 -0.1488 0.0021 1.0000 28.500 1.2290 0.30295 0.29996 -0.1552 0.0021 1.0000 29.000 1.2352 0.30994 0.30700 -0.1607 0.0021 1.0000 29.500 1.2428 0.31608 0.31319 -0.1658 0.0021 1.0000 30.000 1.2515 0.32164 0.31878 -0.1708 0.0020 1.0000 30.500 1.2609 0.32662 0.32380 -0.1756 0.0020 1.0000 31.000 1.2710 0.33107 0.32826 -0.1803 0.0020 1.0000 31.500 1.2811 0.33512 0.33234 -0.1849 0.0019 1.0000 32.000 1.2909 0.33919 0.33645 -0.1895 0.0020 1.0000 32.500 1.3021 0.34232 0.33960 -0.1939 0.0019 1.0000 33.000 1.3119 0.34588 0.34319 -0.1985 0.0019 1.0000 33.500 1.3215 0.34946 0.34681 -0.2033 0.0019 1.0000 34.000 1.3311 0.35254 0.34993 -0.2078 0.0019 1.0000 34.500 1.3395 0.35623 0.35368 -0.2127 0.0019 1.0000 35.000 1.3476 0.35987 0.35736 -0.2176 0.0019 1.0000 35.500 1.3545 0.36407 0.36163 -0.2228 0.0019 1.0000 37.000 0.9705 0.54240 0.54116 -0.2215 0.0066 1.0000 37.500 0.9694 0.55104 0.54984 -0.2242 0.0063 1.0000 38.000 0.9681 0.55941 0.55823 -0.2268 0.0061 1.0000 38.500 0.9664 0.56732 0.56617 -0.2294 0.0058 1.0000 39.000 0.9645 0.57480 0.57368 -0.2320 0.0056 1.0000 39.500 0.9622 0.58177 0.58068 -0.2345 0.0055 1.0000 40.000 0.9596 0.58795 0.58690 -0.2369 0.0054 1.0000 41.000 0.9531 0.60488 0.60388 -0.2418 0.0053 1.0000 41.500 0.9496 0.61424 0.61327 -0.2442 0.0050 1.0000 42.000 0.9458 0.62167 0.62073 -0.2464 0.0046 1.0000 42.500 0.9418 0.62796 0.62705 -0.2487 0.0042 1.0000 43.000 0.9374 0.63314 0.63226 -0.2510 0.0041 1.0000 44.000 0.9280 0.65045 0.64963 -0.2552 0.0037 1.0000 44.500 0.9229 0.65685 0.65605 -0.2572 0.0032 1.0000 45.000 0.9174 0.66168 0.66091 -0.2593 0.0030 1.0000 45.500 0.9115 0.66529 0.66455 -0.2614 0.0029 1.0000 46.000 0.9059 0.67541 0.67469 -0.2632 0.0027 1.0000 46.500 0.8999 0.68212 0.68143 -0.2650 0.0024 1.0000 47.000 0.8934 0.68655 0.68589 -0.2668 0.0021 1.0000 47.500 0.8865 0.68932 0.68868 -0.2688 0.0020 1.0000 48.500 0.8729 0.70270 0.70210 -0.2720 0.0018 1.0000 49.000 0.8659 0.70776 0.70719 -0.2736 0.0015 1.0000 49.500 0.8582 0.71039 0.70985 -0.2752 0.0013 1.0000 50.000 0.8501 0.71181 0.71129 -0.2769 0.0012 1.0000 51.000 0.8341 0.72081 0.72033 -0.2797 0.0011 1.0000 51.500 0.8264 0.72596 0.72551 -0.2809 0.0009 1.0000 52.000 0.8178 0.72809 0.72766 -0.2823 0.0008 1.0000 52.500 0.8090 0.72893 0.72852 -0.2836 0.0007 1.0000 53.000 0.7997 0.72853 0.72815 -0.2850 0.0006 1.0000 54.000 0.7813 0.73205 0.73170 -0.2873 0.0006 1.0000 54.500 0.7723 0.73473 0.73440 -0.2882 0.0006 1.0000 55.000 0.7632 0.73654 0.73624 -0.2891 0.0005 1.0000 55.500 0.7535 0.73656 0.73627 -0.2901 0.0004 1.0000 56.000 0.7436 0.73544 0.73517 -0.2910 0.0003 1.0000 56.500 0.7334 0.73362 0.73337 -0.2920 0.0003 1.0000 57.000 0.7229 0.73044 0.73021 -0.2930 0.0003 1.0000 57.500 0.7119 0.72592 0.72570 -0.2940 0.0002 1.0000 58.000 0.7026 0.72916 0.72896 -0.2943 0.0002 1.0000 58.500 0.6923 0.72758 0.72740 -0.2949 0.0002 1.0000 59.000 0.6816 0.72397 0.72380 -0.2956 0.0001 1.0000 60.000 0.6601 0.71821 0.71807 -0.2966 0.0001 1.0000