XFOIL Version 6.94 Calculated polar for: S4061-096-84 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4185 0.00795 0.00307 -0.0866 0.7391 1.0000 0.500 0.4740 0.00807 0.00298 -0.0863 0.7247 1.0000 1.000 0.5295 0.00821 0.00294 -0.0859 0.7096 1.0000 1.500 0.5848 0.00834 0.00294 -0.0856 0.6927 1.0000 2.000 0.6400 0.00848 0.00297 -0.0852 0.6737 1.0000 2.500 0.6951 0.00864 0.00305 -0.0848 0.6543 1.0000 3.000 0.7500 0.00881 0.00318 -0.0845 0.6337 1.0000 3.500 0.8045 0.00903 0.00332 -0.0840 0.6122 1.0000 4.000 0.8587 0.00928 0.00355 -0.0836 0.5885 1.0000 4.500 0.9123 0.00956 0.00381 -0.0830 0.5616 1.0000 5.000 0.9651 0.00989 0.00413 -0.0824 0.5312 1.0000 5.500 1.0168 0.01031 0.00453 -0.0816 0.4957 1.0000 6.000 1.0668 0.01086 0.00501 -0.0806 0.4532 1.0000 6.500 1.1138 0.01163 0.00565 -0.0792 0.3957 1.0000 7.000 1.1571 0.01272 0.00649 -0.0775 0.3279 1.0000 7.500 1.1970 0.01408 0.00756 -0.0754 0.2606 1.0000 8.000 1.2347 0.01556 0.00881 -0.0732 0.2032 1.0000 8.500 1.2706 0.01706 0.01013 -0.0707 0.1552 1.0000 9.000 1.3025 0.01871 0.01163 -0.0677 0.1128 1.0000 9.500 1.3283 0.02050 0.01330 -0.0639 0.0771 1.0000 10.000 1.3382 0.02305 0.01569 -0.0582 0.0442 1.0000 10.500 1.3424 0.02637 0.01902 -0.0528 0.0288 1.0000 11.000 1.3471 0.03000 0.02287 -0.0484 0.0251 1.0000 11.500 1.3577 0.03348 0.02653 -0.0454 0.0222 1.0000 12.000 1.3565 0.03836 0.03156 -0.0426 0.0205 1.0000 12.500 1.3596 0.04329 0.03673 -0.0403 0.0195 1.0000 13.000 1.3669 0.04811 0.04181 -0.0387 0.0188 1.0000 13.500 1.3731 0.05336 0.04735 -0.0375 0.0180 1.0000 14.000 1.3771 0.05917 0.05346 -0.0367 0.0174 1.0000 14.500 1.3773 0.06579 0.06040 -0.0367 0.0169 1.0000 15.000 1.3730 0.07324 0.06814 -0.0378 0.0163 1.0000 15.500 1.3651 0.08159 0.07676 -0.0398 0.0157 1.0000 16.000 1.3487 0.09195 0.08745 -0.0431 0.0154 1.0000 16.500 1.3242 0.10443 0.10033 -0.0485 0.0153 1.0000 17.000 1.2958 0.11866 0.11496 -0.0562 0.0153 1.0000 17.500 1.2644 0.13485 0.13154 -0.0662 0.0154 1.0000 18.000 1.2069 0.16041 0.15764 -0.0834 0.0161 1.0000 20.000 0.8446 0.24517 0.24306 -0.1221 0.0298 1.0000 20.500 0.8562 0.25229 0.25022 -0.1246 0.0279 1.0000 21.000 0.8711 0.26227 0.26024 -0.1260 0.0266 1.0000 21.500 0.8688 0.27241 0.27038 -0.1322 0.0259 1.0000 22.000 0.8738 0.28195 0.27994 -0.1367 0.0222 1.0000 22.500 0.8854 0.28918 0.28721 -0.1389 0.0206 1.0000 23.000 0.8961 0.29991 0.29795 -0.1413 0.0199 1.0000 23.500 0.8950 0.31113 0.30917 -0.1474 0.0177 1.0000 24.000 0.9038 0.31916 0.31724 -0.1503 0.0156 1.0000 24.500 0.9165 0.32865 0.32677 -0.1519 0.0149 1.0000 25.000 0.9157 0.34104 0.33915 -0.1577 0.0133 1.0000 25.500 0.9225 0.35077 0.34890 -0.1610 0.0120 1.0000 26.000 0.9297 0.35962 0.35778 -0.1639 0.0113 1.0000 26.500 0.9400 0.36948 0.36768 -0.1658 0.0109 1.0000 27.000 0.9415 0.38088 0.37907 -0.1704 0.0107 1.0000 27.500 0.9461 0.39195 0.39018 -0.1742 0.0100 1.0000 28.000 0.9517 0.40223 0.40049 -0.1775 0.0087 1.0000 28.500 0.9574 0.41099 0.40928 -0.1801 0.0078 1.0000 29.000 0.9637 0.42146 0.41978 -0.1826 0.0077 1.0000 29.500 0.9662 0.43298 0.43131 -0.1866 0.0076 1.0000 30.000 0.9701 0.44537 0.44371 -0.1901 0.0065 1.0000 30.500 0.9741 0.45570 0.45407 -0.1932 0.0063 1.0000 31.000 0.9776 0.46615 0.46456 -0.1962 0.0057 1.0000 31.500 0.9807 0.47610 0.47454 -0.1992 0.0054 1.0000 32.000 0.9839 0.48611 0.48459 -0.2020 0.0052 1.0000 32.500 0.9863 0.49735 0.49584 -0.2048 0.0051 1.0000 33.000 0.9880 0.50886 0.50736 -0.2081 0.0050 1.0000