XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY NLF 0414F AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.4818 0.11163 0.10851 -0.0326 0.7979 0.0098 -11.750 -0.4833 0.10682 0.10371 -0.0350 0.7976 0.0097 -11.500 -0.4873 0.10129 0.09819 -0.0379 0.7973 0.0096 -11.250 -0.4948 0.09480 0.09172 -0.0416 0.7971 0.0096 -11.000 -0.5067 0.08688 0.08382 -0.0467 0.7968 0.0095 -10.750 -0.5398 0.07085 0.06776 -0.0603 0.7965 0.0093 -10.500 -0.5755 0.06090 0.05763 -0.0666 0.7960 0.0092 -10.250 -0.6083 0.05330 0.04979 -0.0688 0.7956 0.0091 -10.000 -0.6461 0.04518 0.04128 -0.0687 0.7950 0.0091 -9.750 -0.6801 0.03511 0.03037 -0.0667 0.7944 0.0092 -9.500 -0.6759 0.03094 0.02569 -0.0657 0.7941 0.0094 -9.250 -0.6617 0.02837 0.02273 -0.0651 0.7937 0.0095 -9.000 -0.6429 0.02648 0.02055 -0.0649 0.7935 0.0096 -8.750 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0.3996 0.01254 0.00786 -0.0735 0.7673 0.7723 1.000 0.4292 0.01251 0.00782 -0.0741 0.7663 0.7733 1.250 0.4582 0.01242 0.00774 -0.0744 0.7655 0.7741 1.500 0.4875 0.01228 0.00760 -0.0747 0.7645 0.7747 1.750 0.5171 0.01209 0.00740 -0.0750 0.7635 0.7751 2.000 0.5457 0.01207 0.00743 -0.0755 0.7592 0.7756 2.250 0.5751 0.01178 0.00717 -0.0758 0.7542 0.7763 2.500 0.6058 0.01116 0.00653 -0.0759 0.7503 0.7769 2.750 0.6354 0.01083 0.00623 -0.0762 0.7438 0.7773 3.000 0.6656 0.01041 0.00584 -0.0766 0.7356 0.7778 3.250 0.6949 0.01025 0.00574 -0.0772 0.7192 0.7782 3.500 0.7257 0.00941 0.00476 -0.0771 0.6760 0.7785 3.750 0.7446 0.00980 0.00449 -0.0754 0.5704 0.7792 4.000 0.7574 0.01106 0.00523 -0.0738 0.4682 0.7800 4.250 0.7693 0.01225 0.00599 -0.0722 0.3795 0.7807 4.500 0.7804 0.01339 0.00673 -0.0706 0.2980 0.7812 4.750 0.7902 0.01444 0.00745 -0.0687 0.2307 0.7817 5.000 0.8033 0.01531 0.00805 -0.0672 0.1797 0.7824 5.250 0.8216 0.01600 0.00856 -0.0663 0.1471 0.7830 5.500 0.8409 0.01660 0.00904 -0.0657 0.1224 0.7834 5.750 0.8608 0.01716 0.00949 -0.0650 0.1022 0.7837 6.000 0.8807 0.01770 0.00995 -0.0643 0.0853 0.7841 6.250 0.9006 0.01824 0.01041 -0.0636 0.0719 0.7846 6.500 0.9206 0.01877 0.01089 -0.0629 0.0615 0.7849 6.750 0.9406 0.01928 0.01136 -0.0623 0.0536 0.7851 7.000 0.9603 0.01982 0.01186 -0.0615 0.0475 0.7852 7.250 0.9804 0.02032 0.01236 -0.0609 0.0433 0.7854 7.500 0.9997 0.02089 0.01291 -0.0601 0.0399 0.7856 7.750 1.0198 0.02138 0.01343 -0.0595 0.0377 0.7857 8.000 1.0391 0.02194 0.01398 -0.0587 0.0355 0.7859 8.250 1.0575 0.02256 0.01461 -0.0578 0.0335 0.7860 8.500 1.0767 0.02312 0.01520 -0.0571 0.0322 0.7862 8.750 1.0955 0.02369 0.01581 -0.0563 0.0307 0.7863 9.000 1.1137 0.02432 0.01645 -0.0555 0.0294 0.7865 9.250 1.1309 0.02502 0.01716 -0.0545 0.0283 0.7868 9.500 1.1473 0.02578 0.01794 -0.0534 0.0274 0.7870 9.750 1.1650 0.02644 0.01866 -0.0526 0.0267 0.7872 10.000 1.1819 0.02716 0.01943 -0.0516 0.0260 0.7873 10.250 1.1984 0.02790 0.02023 -0.0506 0.0252 0.7874 10.500 1.2146 0.02867 0.02103 -0.0497 0.0245 0.7875 10.750 1.2303 0.02947 0.02186 -0.0487 0.0238 0.7876 11.000 1.2446 0.03038 0.02280 -0.0475 0.0231 0.7877 11.250 1.2574 0.03142 0.02388 -0.0462 0.0225 0.7878 11.500 1.2719 0.03231 0.02486 -0.0452 0.0222 0.7880 11.750 1.2858 0.03326 0.02588 -0.0440 0.0218 0.7881 12.000 1.2993 0.03425 0.02694 -0.0429 0.0214 0.7883 12.250 1.3125 0.03528 0.02804 -0.0418 0.0209 0.7884 12.500 1.3246 0.03637 0.02921 -0.0406 0.0206 0.7885 12.750 1.3365 0.03750 0.03041 -0.0395 0.0202 0.7887 13.000 1.3482 0.03867 0.03164 -0.0384 0.0198 0.7888 13.250 1.3594 0.03991 0.03295 -0.0373 0.0195 0.7890 13.500 1.3691 0.04127 0.03438 -0.0362 0.0191 0.7891 13.750 1.3771 0.04282 0.03598 -0.0349 0.0188 0.7893 14.000 1.3838 0.04452 0.03776 -0.0337 0.0184 0.7894 14.250 1.3933 0.04600 0.03935 -0.0327 0.0182 0.7895 14.500 1.4018 0.04760 0.04107 -0.0317 0.0180 0.7897 14.750 1.4090 0.04934 0.04292 -0.0307 0.0178 0.7898 15.000 1.4157 0.05117 0.04486 -0.0298 0.0175 0.7900 15.250 1.4215 0.05314 0.04695 -0.0289 0.0173 0.7901 15.500 1.4266 0.05522 0.04914 -0.0281 0.0171 0.7903 15.750 1.4309 0.05744 0.05147 -0.0274 0.0169 0.7904 16.000 1.4342 0.05980 0.05396 -0.0268 0.0167 0.7906 16.250 1.4368 0.06231 0.05658 -0.0263 0.0165 0.7907 16.500 1.4386 0.06498 0.05936 -0.0260 0.0163 0.7908 16.750 1.4396 0.06783 0.06233 -0.0258 0.0161 0.7910 17.000 1.4395 0.07089 0.06550 -0.0258 0.0160 0.7911 17.250 1.4383 0.07416 0.06889 -0.0259 0.0159 0.7913 17.500 1.4358 0.07769 0.07254 -0.0263 0.0157 0.7914 17.750 1.4321 0.08148 0.07646 -0.0269 0.0156 0.7915 18.000 1.4272 0.08557 0.08068 -0.0277 0.0155 0.7917 18.250 1.4208 0.08998 0.08521 -0.0288 0.0154 0.7918 18.500 1.4128 0.09472 0.09008 -0.0302 0.0153 0.7919 18.750 1.4032 0.09983 0.09532 -0.0319 0.0152 0.7921 19.000 1.3926 0.10527 0.10089 -0.0340 0.0151 0.7923 19.250 1.3799 0.11120 0.10696 -0.0365 0.0150 0.7924