XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY LS(1)-0417MOD 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -0.8663 0.07588 0.07197 -0.0628 1.0000 0.0210 -15.750 -0.8934 0.06823 0.06407 -0.0673 1.0000 0.0210 -15.500 -0.9090 0.06290 0.05857 -0.0700 1.0000 0.0210 -15.250 -0.9201 0.05860 0.05412 -0.0717 1.0000 0.0211 -15.000 -0.9277 0.05494 0.05034 -0.0728 1.0000 0.0212 -14.750 -0.9325 0.05177 0.04705 -0.0734 1.0000 0.0213 -14.500 -0.9357 0.04889 0.04405 -0.0738 1.0000 0.0214 -14.250 -0.9353 0.04647 0.04154 -0.0738 1.0000 0.0215 -14.000 -0.9343 0.04417 0.03915 -0.0736 1.0000 0.0217 -13.750 -0.9326 0.04204 0.03691 -0.0732 1.0000 0.0219 -13.500 -0.9307 0.03999 0.03475 -0.0726 1.0000 0.0221 -13.250 -0.9280 0.03810 0.03275 -0.0717 1.0000 0.0223 -13.000 -0.9250 0.03637 0.03089 -0.0705 1.0000 0.0225 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0.3590 0.7248 1.500 0.5975 0.01237 0.00568 -0.0851 0.3525 0.7275 1.750 0.6266 0.01250 0.00580 -0.0853 0.3473 0.7302 2.000 0.6565 0.01258 0.00587 -0.0857 0.3423 0.7326 2.250 0.6861 0.01270 0.00593 -0.0861 0.3368 0.7346 2.500 0.7151 0.01290 0.00605 -0.0864 0.3311 0.7364 2.750 0.7447 0.01304 0.00617 -0.0868 0.3266 0.7381 3.000 0.7739 0.01304 0.00619 -0.0871 0.3220 0.7400 3.250 0.8023 0.01314 0.00627 -0.0872 0.3172 0.7416 3.500 0.8299 0.01333 0.00641 -0.0872 0.3122 0.7431 3.750 0.8578 0.01350 0.00658 -0.0872 0.3076 0.7448 4.000 0.8864 0.01360 0.00671 -0.0873 0.3035 0.7468 4.250 0.9147 0.01373 0.00684 -0.0874 0.2990 0.7487 4.500 0.9425 0.01392 0.00698 -0.0875 0.2943 0.7506 4.750 0.9701 0.01415 0.00718 -0.0876 0.2896 0.7525 5.000 0.9990 0.01425 0.00731 -0.0878 0.2857 0.7544 5.250 1.0275 0.01438 0.00745 -0.0880 0.2813 0.7563 5.500 1.0552 0.01459 0.00761 -0.0881 0.2768 0.7581 5.750 1.0821 0.01487 0.00785 -0.0881 0.2721 0.7599 6.000 1.1098 0.01494 0.00799 -0.0881 0.2684 0.7620 6.250 1.1367 0.01508 0.00815 -0.0880 0.2641 0.7638 6.500 1.1628 0.01530 0.00835 -0.0878 0.2597 0.7656 6.750 1.1882 0.01560 0.00864 -0.0875 0.2551 0.7676 7.000 1.2153 0.01573 0.00884 -0.0874 0.2513 0.7696 7.250 1.2417 0.01592 0.00904 -0.0872 0.2468 0.7718 7.500 1.2670 0.01619 0.00929 -0.0869 0.2424 0.7741 7.750 1.2924 0.01648 0.00958 -0.0867 0.2380 0.7764 8.000 1.3189 0.01667 0.00981 -0.0866 0.2338 0.7786 8.250 1.3439 0.01691 0.01006 -0.0862 0.2293 0.7810 8.500 1.3661 0.01729 0.01040 -0.0854 0.2245 0.7834 8.750 1.3911 0.01746 0.01067 -0.0850 0.2206 0.7858 9.000 1.4148 0.01771 0.01096 -0.0844 0.2161 0.7882 9.250 1.4364 0.01809 0.01132 -0.0835 0.2115 0.7909 9.500 1.4592 0.01840 0.01168 -0.0828 0.2072 0.7937 9.750 1.4818 0.01869 0.01201 -0.0821 0.2025 0.7966 10.000 1.5017 0.01912 0.01241 -0.0810 0.1979 0.7992 10.250 1.5207 0.01946 0.01281 -0.0796 0.1937 0.8021 10.500 1.5379 0.01979 0.01320 -0.0779 0.1893 0.8049 10.750 1.5540 0.02029 0.01371 -0.0762 0.1848 0.8080 11.000 1.5725 0.02076 0.01424 -0.0749 0.1805 0.8114 11.250 1.5912 0.02124 0.01476 -0.0738 0.1757 0.8149 11.500 1.6065 0.02194 0.01544 -0.0723 0.1712 0.8184 11.750 1.6248 0.02242 0.01601 -0.0711 0.1669 0.8220 12.000 1.6403 0.02307 0.01670 -0.0696 0.1623 0.8257 12.250 1.6536 0.02389 0.01754 -0.0680 0.1581 0.8297 12.500 1.6706 0.02454 0.01826 -0.0669 0.1536 0.8338 12.750 1.6833 0.02546 0.01920 -0.0654 0.1493 0.8376 13.000 1.6965 0.02632 0.02013 -0.0640 0.1452 0.8415 13.250 1.7094 0.02724 0.02112 -0.0626 0.1409 0.8456 13.500 1.7177 0.02853 0.02242 -0.0610 0.1370 0.8502 13.750 1.7318 0.02948 0.02345 -0.0600 0.1329 0.8547 14.000 1.7397 0.03081 0.02483 -0.0584 0.1289 0.8590 14.250 1.7488 0.03213 0.02623 -0.0572 0.1248 0.8639 14.500 1.7568 0.03362 0.02776 -0.0560 0.1205 0.8691 14.750 1.7618 0.03534 0.02953 -0.0547 0.1165 0.8740 15.000 1.7686 0.03695 0.03122 -0.0536 0.1124 0.8797 15.500 1.7742 0.04102 0.03546 -0.0514 0.1059 0.8921 15.750 1.7748 0.04338 0.03790 -0.0505 0.1030 0.8994 16.000 1.7700 0.04630 0.04090 -0.0496 0.1006 0.9068 16.250 1.7717 0.04869 0.04342 -0.0490 0.0980 0.9162 16.500 1.7667 0.05173 0.04657 -0.0484 0.0956 0.9289 16.750 1.7521 0.05530 0.05026 -0.0472 0.0938 1.0000 17.000 1.7473 0.05919 0.05427 -0.0479 0.0916 1.0000 17.250 1.7403 0.06349 0.05868 -0.0489 0.0894 1.0000 17.500 1.7275 0.06874 0.06402 -0.0504 0.0875 1.0000 17.750 1.7078 0.07510 0.07047 -0.0523 0.0859 1.0000 18.000 1.6960 0.08042 0.07594 -0.0541 0.0841 1.0000 18.250 1.6804 0.08628 0.08191 -0.0561 0.0823 1.0000 18.500 1.6606 0.09276 0.08849 -0.0583 0.0807 1.0000