XFOIL Version 6.96 Calculated polar for: FX 68-H-120 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3899 0.11462 0.10826 -0.0151 1.0000 0.2240 -9.750 -0.3852 0.11137 0.10503 -0.0159 1.0000 0.2320 -9.500 -0.3909 0.10815 0.10191 -0.0175 1.0000 0.2369 -9.250 -0.3818 0.10448 0.09826 -0.0175 1.0000 0.2468 -9.000 -0.3743 0.10076 0.09458 -0.0174 1.0000 0.2582 -8.750 -0.3718 0.09754 0.09143 -0.0174 1.0000 0.2726 -8.500 -0.3699 0.09429 0.08823 -0.0172 1.0000 0.2857 -8.250 -0.3941 0.09287 0.08698 -0.0185 1.0000 0.2924 -8.000 -0.5222 0.07409 0.06838 -0.0379 1.0000 0.1208 -7.750 -0.5302 0.07100 0.06530 -0.0354 1.0000 0.1199 -7.500 -0.5426 0.06772 0.06201 -0.0329 1.0000 0.1189 -7.250 -0.5560 0.06412 0.05833 -0.0305 1.0000 0.1176 -7.000 -0.5682 0.06027 0.05434 -0.0281 1.0000 0.1163 -6.750 -0.5785 0.05610 0.04993 -0.0257 1.0000 0.1151 -6.500 -0.5851 0.05191 0.04541 -0.0232 1.0000 0.1148 -6.250 -0.5874 0.04786 0.04094 -0.0206 1.0000 0.1161 -6.000 -0.5873 0.04384 0.03629 -0.0179 1.0000 0.1195 -5.750 -0.5762 0.04216 0.03457 -0.0156 1.0000 0.1303 -5.500 -0.5663 0.03965 0.03178 -0.0131 1.0000 0.1415 -5.250 -0.5552 0.03755 0.02930 -0.0106 1.0000 0.1599 -5.000 -0.5422 0.03571 0.02735 -0.0082 1.0000 0.1839 -4.750 -0.5290 0.03436 0.02591 -0.0057 1.0000 0.2152 -4.500 -0.5147 0.03311 0.02453 -0.0034 1.0000 0.2461 -4.250 -0.4985 0.03198 0.02333 -0.0015 1.0000 0.2724 -4.000 -0.4810 0.03078 0.02188 0.0002 1.0000 0.2948 -3.750 -0.4617 0.02974 0.02075 0.0016 1.0000 0.3135 -3.500 -0.4419 0.02879 0.01962 0.0028 1.0000 0.3312 -3.250 -0.4209 0.02788 0.01852 0.0038 1.0000 0.3471 -3.000 -0.3997 0.02710 0.01752 0.0048 1.0000 0.3641 -2.750 -0.3772 0.02637 0.01667 0.0054 1.0000 0.3802 -2.500 -0.3541 0.02571 0.01602 0.0060 1.0000 0.3993 -2.250 -0.3301 0.02517 0.01539 0.0064 1.0000 0.4221 -2.000 -0.3042 0.02464 0.01491 0.0064 1.0000 0.4501 -1.750 -0.2797 0.02407 0.01452 0.0067 1.0000 0.4921 -1.500 -0.1403 0.02263 0.01470 -0.0121 1.0000 1.0000 -1.250 -0.1271 0.02283 0.01453 -0.0106 1.0000 1.0000 -1.000 -0.1141 0.02310 0.01450 -0.0091 1.0000 1.0000 -0.750 -0.1012 0.02344 0.01461 -0.0076 1.0000 1.0000 -0.500 -0.0884 0.02385 0.01482 -0.0062 1.0000 1.0000 -0.250 -0.0760 0.02434 0.01514 -0.0049 1.0000 1.0000 0.000 -0.0336 0.02545 0.01606 -0.0095 0.9888 1.0000 0.250 0.0430 0.02709 0.01748 -0.0201 0.9617 1.0000 0.500 0.1149 0.02837 0.01860 -0.0291 0.9333 1.0000 0.750 0.1855 0.02925 0.01941 -0.0372 0.9041 1.0000 1.000 0.2505 0.02969 0.01979 -0.0435 0.8743 1.0000 1.250 0.3120 0.02971 0.01982 -0.0487 0.8436 1.0000 1.500 0.3738 0.02924 0.01938 -0.0530 0.8135 1.0000 1.750 0.4235 0.02841 0.01857 -0.0545 0.7838 1.0000 2.000 0.4653 0.02738 0.01756 -0.0543 0.7546 1.0000 2.250 0.5013 0.02625 0.01640 -0.0529 0.7253 1.0000 2.500 0.5340 0.02508 0.01518 -0.0508 0.6956 1.0000 2.750 0.5648 0.02396 0.01399 -0.0485 0.6652 1.0000 3.000 0.5897 0.02336 0.01323 -0.0458 0.6304 1.0000 3.250 0.6159 0.02296 0.01258 -0.0435 0.5970 1.0000 3.500 0.6406 0.02302 0.01234 -0.0414 0.5644 1.0000 3.750 0.6632 0.02353 0.01265 -0.0397 0.5335 1.0000 4.000 0.6864 0.02422 0.01310 -0.0382 0.5066 1.0000 4.250 0.7088 0.02506 0.01379 -0.0369 0.4826 1.0000 4.500 0.7311 0.02603 0.01465 -0.0358 0.4625 1.0000 4.750 0.7526 0.02705 0.01565 -0.0347 0.4445 1.0000 5.000 0.7744 0.02809 0.01669 -0.0336 0.4285 1.0000 5.250 0.7957 0.02919 0.01779 -0.0326 0.4145 1.0000 5.500 0.8169 0.03040 0.01905 -0.0317 0.4029 1.0000 5.750 0.8402 0.03159 0.02020 -0.0309 0.3933 1.0000 6.000 0.8577 0.03306 0.02192 -0.0298 0.3837 1.0000 6.250 0.8757 0.03457 0.02357 -0.0286 0.3752 1.0000 6.500 0.8968 0.03586 0.02491 -0.0277 0.3671 1.0000 6.750 0.9088 0.03783 0.02715 -0.0263 0.3603 1.0000 7.000 0.9245 0.03966 0.02916 -0.0251 0.3548 1.0000 7.250 0.9443 0.04144 0.03103 -0.0243 0.3504 1.0000 7.500 0.9426 0.04456 0.03455 -0.0223 0.3467 1.0000 7.750 0.9434 0.04756 0.03783 -0.0205 0.3430 1.0000 8.000 0.9541 0.04991 0.04038 -0.0192 0.3392 1.0000 8.250 0.9596 0.05277 0.04339 -0.0178 0.3359 1.0000 8.500 0.9237 0.05857 0.04942 -0.0151 0.3348 1.0000 8.750 0.8712 0.06609 0.05694 -0.0131 0.3356 1.0000 10.750 1.1505 0.05169 0.04317 -0.0012 0.2226 1.0000 11.000 1.1285 0.05509 0.04694 0.0023 0.2199 1.0000 11.250 1.0852 0.06198 0.05409 0.0052 0.2256 1.0000 11.500 1.0623 0.06630 0.05853 0.0069 0.2246 1.0000 11.750 1.0394 0.07130 0.06363 0.0074 0.2235 1.0000 12.000 1.1395 0.05302 0.04536 0.0138 0.1760 1.0000 12.250 1.1343 0.05382 0.04624 0.0158 0.1655 1.0000 12.500 1.1144 0.05740 0.05007 0.0165 0.1588 1.0000 12.750 1.0984 0.06083 0.05363 0.0166 0.1506 1.0000 13.000 1.0721 0.06688 0.05992 0.0150 0.1468 1.0000 13.250 1.0588 0.07122 0.06436 0.0135 0.1391 1.0000 13.500 1.0296 0.07937 0.07268 0.0100 0.1393 1.0000 13.750 0.9967 0.08901 0.08234 0.0056 0.1402 1.0000