XFOIL Version 6.96 Calculated polar for: FX 77-W-121 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.3140 0.11286 0.10719 -0.0208 0.6106 0.0439 -9.500 -0.3141 0.11009 0.10444 -0.0241 0.6053 0.0442 -9.250 -0.3127 0.10717 0.10151 -0.0270 0.6006 0.0444 -9.000 -0.3087 0.10363 0.09797 -0.0291 0.5962 0.0444 -8.750 -0.2895 0.09800 0.09229 -0.0257 0.5900 0.0465 -8.500 -0.2788 0.09502 0.08927 -0.0257 0.5856 0.0486 -8.250 -0.2744 0.09186 0.08609 -0.0271 0.5823 0.0497 -8.000 -0.2710 0.08882 0.08309 -0.0286 0.5786 0.0510 -7.750 -0.2703 0.08555 0.07984 -0.0304 0.5755 0.0520 -7.500 -0.2706 0.08238 0.07668 -0.0322 0.5727 0.0524 -7.250 -0.2745 0.07925 0.07355 -0.0338 0.5704 0.0534 -7.000 -0.2727 0.07580 0.07006 -0.0358 0.5680 0.0534 -6.750 -0.2680 0.07230 0.06655 -0.0378 0.5651 0.0532 -6.500 -0.2680 0.06357 0.05755 -0.0431 0.5640 0.0325 -6.250 -0.2600 0.06006 0.05397 -0.0432 0.5613 0.0316 -6.000 -0.2503 0.05656 0.05033 -0.0436 0.5588 0.0307 -5.750 -0.2397 0.05281 0.04637 -0.0438 0.5564 0.0299 -5.500 -0.2281 0.04888 0.04217 -0.0436 0.5544 0.0294 -5.250 -0.2150 0.04512 0.03810 -0.0430 0.5520 0.0289 -5.000 -0.2001 0.04171 0.03434 -0.0421 0.5492 0.0291 -4.750 -0.1835 0.03872 0.03096 -0.0409 0.5466 0.0304 -4.500 -0.1658 0.03587 0.02761 -0.0394 0.5443 0.0316 -4.250 -0.1469 0.03325 0.02448 -0.0378 0.5421 0.0321 -4.000 -0.1262 0.03094 0.02162 -0.0362 0.5402 0.0326 -3.750 -0.1037 0.02911 0.01929 -0.0349 0.5385 0.0331 -3.500 -0.0810 0.02722 0.01717 -0.0341 0.5362 0.0348 -3.250 -0.0567 0.02631 0.01614 -0.0336 0.5337 0.0380 -3.000 -0.0308 0.02512 0.01464 -0.0329 0.5312 0.0404 -2.750 -0.0038 0.02393 0.01316 -0.0323 0.5289 0.0424 -2.500 0.0228 0.02299 0.01201 -0.0318 0.5267 0.0457 -2.250 0.0486 0.02225 0.01123 -0.0314 0.5250 0.0501 -2.000 0.0747 0.02158 0.01042 -0.0308 0.5234 0.0536 -1.750 0.0997 0.02106 0.00986 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3.250 0.7212 0.02172 0.01169 -0.0469 0.4808 1.0000 3.500 0.7460 0.02200 0.01191 -0.0464 0.4791 1.0000 3.750 0.7669 0.02269 0.01274 -0.0459 0.4758 1.0000 4.000 0.7888 0.02328 0.01343 -0.0453 0.4728 1.0000 4.250 0.8115 0.02374 0.01393 -0.0447 0.4701 1.0000 4.500 0.8350 0.02411 0.01432 -0.0441 0.4679 1.0000 4.750 0.8593 0.02439 0.01459 -0.0436 0.4658 1.0000 5.000 0.8836 0.02471 0.01493 -0.0430 0.4639 1.0000 5.250 0.9004 0.02572 0.01616 -0.0422 0.4591 1.0000 5.500 0.9218 0.02623 0.01676 -0.0415 0.4555 1.0000 6.000 0.9707 0.02661 0.01720 -0.0403 0.4505 1.0000 6.250 0.9879 0.02753 0.01830 -0.0394 0.4462 1.0000 6.500 1.0054 0.02834 0.01927 -0.0385 0.4416 1.0000 6.750 1.0283 0.02862 0.01962 -0.0377 0.4385 1.0000 7.000 1.0539 0.02865 0.01972 -0.0372 0.4361 1.0000 7.250 1.0680 0.02970 0.02096 -0.0360 0.4309 1.0000 7.500 1.0842 0.03047 0.02190 -0.0349 0.4257 1.0000 7.750 1.1087 0.03051 0.02202 -0.0342 0.4227 1.0000 8.000 1.1363 0.03033 0.02193 -0.0337 0.4205 1.0000 8.250 1.1351 0.03249 0.02440 -0.0316 0.4123 1.0000 8.500 1.1564 0.03274 0.02477 -0.0308 0.4087 1.0000 8.750 1.1842 0.03245 0.02458 -0.0302 0.4062 1.0000 9.000 1.1737 0.03510 0.02751 -0.0276 0.3971 1.0000 9.250 1.1966 0.03506 0.02759 -0.0266 0.3934 1.0000 9.500 1.2108 0.03567 0.02840 -0.0253 0.3888 1.0000 9.750 1.1248 0.04425 0.03699 -0.0212 0.3714 1.0000 10.250 1.1113 0.05049 0.04338 -0.0209 0.3530 1.0000 10.500 1.1385 0.04957 0.04265 -0.0197 0.3510 1.0000 11.000 1.1494 0.05306 0.04637 -0.0188 0.3368 1.0000 11.500 1.1504 0.05784 0.05135 -0.0183 0.3195 1.0000 11.750 1.1689 0.05761 0.05127 -0.0175 0.3098 1.0000 12.000 1.1897 0.05675 0.05050 -0.0167 0.2921 1.0000 12.250 1.1942 0.05825 0.05197 -0.0163 0.2716 1.0000 12.500 1.2000 0.05950 0.05310 -0.0157 0.2464 1.0000 12.750 1.1977 0.06187 0.05530 -0.0153 0.2204 1.0000 13.000 1.1883 0.06531 0.05859 -0.0153 0.1953 1.0000 13.250 1.1770 0.06932 0.06246 -0.0156 0.1694 1.0000 13.500 1.1644 0.07369 0.06664 -0.0162 0.1392 1.0000 13.750 1.1495 0.07855 0.07127 -0.0170 0.1098 1.0000 14.000 1.1314 0.08405 0.07653 -0.0181 0.0824 1.0000 14.250 1.1155 0.08944 0.08173 -0.0192 0.0601 1.0000 14.500 1.1029 0.09456 0.08676 -0.0203 0.0476 1.0000