XFOIL Version 6.94 Calculated polar for: SELIG 3002-099-83 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 0.3940 0.00839 0.00359 -0.0815 0.7905 0.8532 0.500 0.4391 0.00827 0.00347 -0.0781 0.7678 0.8874 1.000 0.4861 0.00813 0.00327 -0.0754 0.7430 0.9132 2.000 0.5921 0.00798 0.00293 -0.0732 0.6829 0.9587 2.500 0.6589 0.00809 0.00290 -0.0755 0.6430 1.0000 3.000 0.7165 0.00843 0.00302 -0.0761 0.5972 1.0000 3.500 0.7724 0.00890 0.00324 -0.0764 0.5438 1.0000 4.000 0.8264 0.00948 0.00357 -0.0763 0.4870 1.0000 4.500 0.8788 0.01015 0.00399 -0.0760 0.4325 1.0000 5.000 0.9301 0.01089 0.00451 -0.0754 0.3829 1.0000 5.500 0.9805 0.01167 0.00509 -0.0747 0.3374 1.0000 6.000 1.0302 0.01247 0.00576 -0.0740 0.2948 1.0000 6.500 1.0789 0.01333 0.00648 -0.0730 0.2547 1.0000 7.000 1.1260 0.01429 0.00731 -0.0719 0.2171 1.0000 7.500 1.1717 0.01533 0.00824 -0.0706 0.1831 1.0000 8.000 1.2164 0.01644 0.00930 -0.0691 0.1537 1.0000 8.500 1.2585 0.01769 0.01051 -0.0674 0.1273 1.0000 9.000 1.2970 0.01915 0.01192 -0.0651 0.1054 1.0000 9.500 1.3308 0.02088 0.01363 -0.0622 0.0879 1.0000 10.000 1.3610 0.02263 0.01546 -0.0588 0.0757 1.0000 10.500 1.3883 0.02423 0.01724 -0.0550 0.0673 1.0000 11.000 1.4040 0.02678 0.01987 -0.0502 0.0608 1.0000 11.500 1.4264 0.02883 0.02213 -0.0467 0.0555 1.0000 12.000 1.4353 0.03250 0.02588 -0.0427 0.0504 1.0000 12.500 1.4532 0.03524 0.02894 -0.0399 0.0474 1.0000 13.000 1.4656 0.03863 0.03254 -0.0375 0.0439 1.0000 13.500 1.4699 0.04353 0.03757 -0.0353 0.0408 1.0000 14.000 1.4744 0.04853 0.04294 -0.0339 0.0388 1.0000 14.500 1.4749 0.05408 0.04883 -0.0335 0.0366 1.0000 15.000 1.4721 0.06038 0.05538 -0.0341 0.0346 1.0000 15.500 1.4654 0.06776 0.06297 -0.0355 0.0331 1.0000 16.000 1.4429 0.07844 0.07399 -0.0381 0.0315 1.0000 16.500 1.4220 0.08941 0.08538 -0.0433 0.0308 1.0000 17.000 1.3950 0.10259 0.09896 -0.0505 0.0300 1.0000 17.500 1.3600 0.11846 0.11522 -0.0599 0.0295 1.0000 18.000 1.3091 0.13933 0.13651 -0.0734 0.0295 1.0000