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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.4564 0.09695 0.09051 -0.0311 1.0000 0.0432 -10.250 -0.4635 0.09099 0.08464 -0.0343 1.0000 0.0433 -10.000 -0.4736 0.08445 0.07819 -0.0381 1.0000 0.0432 -9.750 -0.4858 0.07742 0.07125 -0.0426 1.0000 0.0427 -9.500 -0.5066 0.06908 0.06295 -0.0493 1.0000 0.0419 -9.250 -0.5317 0.06338 0.05723 -0.0523 1.0000 0.0413 -9.000 -0.5572 0.05940 0.05318 -0.0515 1.0000 0.0409 -8.750 -0.5813 0.05597 0.04961 -0.0490 1.0000 0.0407 -8.500 -0.6023 0.05307 0.04653 -0.0453 1.0000 0.0407 -8.250 -0.6190 0.05021 0.04343 -0.0415 1.0000 0.0408 -8.000 -0.6314 0.04725 0.04013 -0.0377 1.0000 0.0414 -7.750 -0.6377 0.04445 0.03696 -0.0342 1.0000 0.0422 -7.500 -0.6395 0.04171 0.03373 -0.0309 1.0000 0.0437 -7.250 -0.6363 0.03958 0.03141 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0.6175 1.0000 2.500 0.5167 0.02049 0.00957 -0.0391 0.5791 1.0000 2.750 0.5395 0.02054 0.00930 -0.0373 0.5411 1.0000 3.000 0.5604 0.02084 0.00930 -0.0355 0.5069 1.0000 3.250 0.5801 0.02129 0.00949 -0.0338 0.4766 1.0000 3.500 0.5997 0.02181 0.00977 -0.0322 0.4509 1.0000 3.750 0.6191 0.02235 0.01016 -0.0307 0.4272 1.0000 4.000 0.6388 0.02291 0.01058 -0.0293 0.4069 1.0000 4.250 0.6588 0.02348 0.01106 -0.0280 0.3881 1.0000 4.500 0.6791 0.02405 0.01154 -0.0267 0.3713 1.0000 4.750 0.6998 0.02464 0.01205 -0.0255 0.3561 1.0000 5.000 0.7210 0.02524 0.01264 -0.0245 0.3425 1.0000 5.250 0.7429 0.02586 0.01323 -0.0235 0.3305 1.0000 5.500 0.7652 0.02649 0.01382 -0.0226 0.3195 1.0000 5.750 0.7875 0.02712 0.01443 -0.0218 0.3092 1.0000 6.000 0.8094 0.02780 0.01519 -0.0209 0.2991 1.0000 6.250 0.8323 0.02850 0.01594 -0.0201 0.2911 1.0000 6.500 0.8550 0.02926 0.01678 -0.0194 0.2836 1.0000 6.750 0.8782 0.03005 0.01761 -0.0187 0.2772 1.0000 7.000 0.8998 0.03089 0.01859 -0.0179 0.2704 1.0000 7.250 0.9229 0.03168 0.01939 -0.0172 0.2649 1.0000 7.500 0.9424 0.03267 0.02067 -0.0162 0.2586 1.0000 7.750 0.9645 0.03355 0.02164 -0.0155 0.2537 1.0000 8.000 0.9860 0.03460 0.02285 -0.0147 0.2497 1.0000 8.250 1.0043 0.03586 0.02440 -0.0137 0.2455 1.0000 8.500 1.0241 0.03704 0.02579 -0.0128 0.2419 1.0000 8.750 1.0461 0.03811 0.02699 -0.0121 0.2387 1.0000 9.000 1.0588 0.03938 0.02856 -0.0105 0.2333 1.0000 9.250 1.0715 0.03933 0.02854 -0.0085 0.2218 1.0000 9.500 1.0764 0.03927 0.02847 -0.0056 0.2084 1.0000 9.750 1.0781 0.03971 0.02906 -0.0027 0.1972 1.0000 10.000 1.0840 0.04068 0.03029 -0.0004 0.1904 1.0000 10.250 1.0840 0.04108 0.03068 0.0027 0.1805 1.0000 10.500 1.0793 0.04221 0.03204 0.0058 0.1718 1.0000 10.750 1.0780 0.04338 0.03335 0.0082 0.1641 1.0000 11.000 1.0745 0.04471 0.03479 0.0103 0.1548 1.0000 11.250 1.0685 0.04674 0.03704 0.0119 0.1432 1.0000 11.500 1.0666 0.04895 0.03949 0.0128 0.1339 1.0000 11.750 1.0648 0.05132 0.04207 0.0135 0.1261 1.0000 12.000 1.0588 0.05452 0.04557 0.0136 0.1140 1.0000 12.250 1.0482 0.05875 0.05016 0.0129 0.1011 1.0000 12.500 1.0305 0.06435 0.05609 0.0113 0.0913 1.0000 13.000 0.9933 0.07575 0.06698 0.0063 0.0459 1.0000 13.500 0.9259 0.09683 0.08908 -0.0030 0.1136 1.0000 13.750 0.9025 0.10533 0.09761 -0.0067 0.1127 1.0000