XFOIL Version 6.96 Calculated polar for: GOE 288 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.6944 0.13306 0.13061 -0.0403 1.0000 0.0232 -18.500 -0.7142 0.12533 0.12279 -0.0448 1.0000 0.0234 -18.250 -0.7289 0.11870 0.11609 -0.0486 1.0000 0.0235 -18.000 -0.7399 0.11290 0.11023 -0.0520 1.0000 0.0237 -17.750 -0.7533 0.10674 0.10400 -0.0556 1.0000 0.0238 -17.500 -0.7668 0.10071 0.09789 -0.0591 1.0000 0.0239 -17.250 -0.7780 0.09514 0.09225 -0.0624 1.0000 0.0240 -17.000 -0.7886 0.08977 0.08682 -0.0656 1.0000 0.0241 -16.750 -0.7995 0.08441 0.08138 -0.0688 1.0000 0.0241 -16.500 -0.8102 0.07919 0.07609 -0.0720 1.0000 0.0242 -16.250 -0.8202 0.07416 0.07099 -0.0751 1.0000 0.0243 -16.000 -0.8291 0.06940 0.06616 -0.0780 1.0000 0.0244 -15.750 -0.8384 0.06470 0.06140 -0.0809 1.0000 0.0244 -15.500 -0.8490 0.06002 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0.4533 0.2645 -0.500 0.6018 0.00901 0.00238 -0.1362 0.4481 0.2806 -0.250 0.6312 0.00904 0.00241 -0.1364 0.4413 0.2921 0.000 0.6601 0.00911 0.00246 -0.1365 0.4336 0.3018 0.250 0.6893 0.00916 0.00250 -0.1367 0.4248 0.3103 0.500 0.7179 0.00927 0.00256 -0.1368 0.4135 0.3174 0.750 0.7460 0.00942 0.00263 -0.1368 0.3985 0.3226 1.000 0.7738 0.00959 0.00273 -0.1368 0.3815 0.3289 1.250 0.8014 0.00978 0.00285 -0.1367 0.3662 0.3353 1.500 0.8291 0.00996 0.00297 -0.1367 0.3533 0.3417 1.750 0.8569 0.01011 0.00309 -0.1367 0.3435 0.3503 2.000 0.8845 0.01029 0.00323 -0.1366 0.3344 0.3585 2.250 0.9125 0.01041 0.00335 -0.1366 0.3282 0.3671 2.500 0.9403 0.01055 0.00347 -0.1366 0.3221 0.3724 2.750 0.9677 0.01073 0.00361 -0.1365 0.3159 0.3761 3.000 0.9958 0.01084 0.00372 -0.1365 0.3119 0.3800 3.250 1.0235 0.01097 0.00384 -0.1365 0.3076 0.3845 3.500 1.0508 0.01112 0.00399 -0.1364 0.3034 0.3896 3.750 1.0780 0.01129 0.00414 -0.1363 0.2994 0.3944 4.000 1.1056 0.01141 0.00427 -0.1363 0.2970 0.3989 4.250 1.1332 0.01151 0.00440 -0.1363 0.2947 0.4041 4.500 1.1605 0.01164 0.00454 -0.1362 0.2922 0.4095 4.750 1.1875 0.01179 0.00469 -0.1361 0.2896 0.4149 5.000 1.2141 0.01194 0.00487 -0.1359 0.2869 0.4222 5.250 1.2404 0.01212 0.00505 -0.1357 0.2839 0.4295 5.750 1.2932 0.01241 0.00540 -0.1353 0.2794 0.4457 6.000 1.3197 0.01254 0.00558 -0.1351 0.2776 0.4567 6.250 1.3458 0.01268 0.00576 -0.1349 0.2757 0.4720 6.500 1.3715 0.01283 0.00597 -0.1346 0.2737 0.4913 6.750 1.3969 0.01298 0.00619 -0.1343 0.2716 0.5167 7.000 1.4218 0.01314 0.00643 -0.1339 0.2695 0.5539 7.250 1.4462 0.01328 0.00672 -0.1335 0.2669 0.6189 7.500 1.4644 0.01289 0.00703 -0.1317 0.2643 1.0000 7.750 1.4892 0.01308 0.00724 -0.1312 0.2630 1.0000 8.000 1.5132 0.01329 0.00747 -0.1307 0.2614 1.0000 8.250 1.5366 0.01351 0.00770 -0.1300 0.2595 1.0000 8.500 1.5590 0.01376 0.00796 -0.1291 0.2571 1.0000 8.750 1.5791 0.01404 0.00825 -0.1279 0.2546 1.0000 9.000 1.5983 0.01437 0.00857 -0.1265 0.2520 1.0000 9.250 1.6171 0.01473 0.00894 -0.1251 0.2496 1.0000 9.500 1.6367 0.01507 0.00930 -0.1239 0.2480 1.0000 9.750 1.6575 0.01537 0.00963 -0.1229 0.2468 1.0000 10.000 1.6777 0.01570 0.00999 -0.1218 0.2443 1.0000 10.250 1.6969 0.01608 0.01039 -0.1207 0.2413 1.0000 10.500 1.7150 0.01653 0.01086 -0.1194 0.2385 1.0000 10.750 1.7317 0.01707 0.01139 -0.1180 0.2353 1.0000 11.000 1.7485 0.01762 0.01196 -0.1166 0.2325 1.0000 11.250 1.7672 0.01808 0.01246 -0.1156 0.2307 1.0000 11.500 1.7850 0.01860 0.01302 -0.1145 0.2278 1.0000 11.750 1.8001 0.01929 0.01372 -0.1131 0.2232 1.0000 12.000 1.8125 0.02017 0.01459 -0.1115 0.2182 1.0000 12.250 1.8287 0.02085 0.01530 -0.1104 0.2149 1.0000 12.500 1.8430 0.02167 0.01615 -0.1091 0.2108 1.0000 12.750 1.8537 0.02275 0.01723 -0.1076 0.2057 1.0000 13.000 1.8651 0.02382 0.01832 -0.1062 0.2002 1.0000 13.250 1.8721 0.02526 0.01975 -0.1046 0.1920 1.0000 13.500 1.8777 0.02686 0.02134 -0.1029 0.1832 1.0000 13.750 1.8742 0.02926 0.02369 -0.1008 0.1692 1.0000 14.000 1.8557 0.03308 0.02740 -0.0981 0.1471 1.0000 14.250 1.8208 0.03870 0.03288 -0.0950 0.1186 1.0000 14.500 1.7930 0.04404 0.03816 -0.0930 0.0993 1.0000 14.750 1.7731 0.04883 0.04294 -0.0917 0.0874 1.0000 15.000 1.7634 0.05265 0.04678 -0.0909 0.0811 1.0000 15.250 1.7541 0.05648 0.05065 -0.0902 0.0765 1.0000 15.500 1.7501 0.05982 0.05405 -0.0897 0.0735 1.0000 15.750 1.7450 0.06333 0.05762 -0.0893 0.0707 1.0000 16.000 1.7375 0.06712 0.06147 -0.0890 0.0681 1.0000 16.250 1.7336 0.07054 0.06495 -0.0887 0.0659 1.0000 16.500 1.7270 0.07437 0.06884 -0.0886 0.0632 1.0000 16.750 1.7175 0.07860 0.07313 -0.0885 0.0605 1.0000 17.000 1.7096 0.08264 0.07722 -0.0885 0.0578 1.0000 17.250 1.7002 0.08695 0.08159 -0.0886 0.0545 1.0000 17.500 1.6876 0.09175 0.08646 -0.0889 0.0516 1.0000 17.750 1.6748 0.09665 0.09141 -0.0894 0.0478 1.0000 18.000 1.6597 0.10190 0.09672 -0.0900 0.0442 1.0000 18.250 1.6442 0.10730 0.10217 -0.0908 0.0406 1.0000 18.500 1.6287 0.11281 0.10775 -0.0917 0.0369 1.0000 18.750 1.6126 0.11845 0.11344 -0.0929 0.0335 1.0000