XFOIL Version 6.96 Calculated polar for: NASA SC(2)-0414 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -1.3443 0.08572 0.08180 -0.0361 1.0000 0.0190 -19.500 -1.3587 0.07982 0.07577 -0.0390 1.0000 0.0191 -19.250 -1.3696 0.07463 0.07046 -0.0415 1.0000 0.0192 -19.000 -1.3772 0.07003 0.06575 -0.0435 1.0000 0.0193 -18.750 -1.3820 0.06594 0.06155 -0.0453 1.0000 0.0193 -18.500 -1.3873 0.06193 0.05745 -0.0468 1.0000 0.0195 -18.250 -1.3927 0.05800 0.05342 -0.0483 1.0000 0.0197 -18.000 -1.3954 0.05455 0.04989 -0.0494 1.0000 0.0199 -17.750 -1.3955 0.05154 0.04680 -0.0502 1.0000 0.0200 -17.500 -1.3936 0.04884 0.04403 -0.0508 1.0000 0.0202 -17.250 -1.3901 0.04637 0.04150 -0.0513 1.0000 0.0204 -17.000 -1.3855 0.04410 0.03916 -0.0517 1.0000 0.0206 -16.750 -1.3794 0.04207 0.03707 -0.0519 1.0000 0.0208 -16.500 -1.3724 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0.00608 0.00169 -0.0847 0.7820 0.5154 -1.750 0.0946 0.00603 0.00168 -0.0855 0.7633 0.5496 -1.500 0.1248 0.00609 0.00168 -0.0858 0.7404 0.5687 -1.250 0.1550 0.00615 0.00169 -0.0862 0.7164 0.5837 -1.000 0.1849 0.00624 0.00171 -0.0864 0.6896 0.5947 -0.750 0.2140 0.00643 0.00175 -0.0866 0.6468 0.6040 -0.500 0.2430 0.00665 0.00179 -0.0867 0.6007 0.6116 -0.250 0.2704 0.00711 0.00193 -0.0866 0.5124 0.6195 0.000 0.2980 0.00758 0.00208 -0.0867 0.4282 0.6254 0.250 0.3258 0.00801 0.00221 -0.0867 0.3560 0.6293 0.500 0.3539 0.00838 0.00236 -0.0868 0.2942 0.6326 0.750 0.3822 0.00872 0.00249 -0.0869 0.2435 0.6357 1.000 0.4106 0.00902 0.00261 -0.0870 0.2044 0.6389 1.250 0.4393 0.00928 0.00273 -0.0871 0.1739 0.6416 1.500 0.4683 0.00948 0.00283 -0.0873 0.1543 0.6434 1.750 0.4973 0.00968 0.00294 -0.0874 0.1370 0.6448 2.000 0.5261 0.00987 0.00305 -0.0876 0.1219 0.6463 2.250 0.5550 0.01005 0.00318 -0.0877 0.1102 0.6480 2.750 0.6126 0.01040 0.00344 -0.0879 0.0920 0.6512 3.000 0.6414 0.01058 0.00358 -0.0880 0.0860 0.6528 3.250 0.6701 0.01075 0.00373 -0.0881 0.0813 0.6545 3.500 0.6987 0.01093 0.00388 -0.0881 0.0770 0.6561 3.750 0.7274 0.01110 0.00403 -0.0882 0.0728 0.6577 4.000 0.7558 0.01130 0.00420 -0.0882 0.0684 0.6594 4.250 0.7842 0.01149 0.00436 -0.0882 0.0648 0.6610 4.500 0.8124 0.01170 0.00453 -0.0882 0.0610 0.6624 4.750 0.8406 0.01189 0.00471 -0.0882 0.0579 0.6641 5.000 0.8685 0.01211 0.00491 -0.0881 0.0546 0.6661 5.250 0.8965 0.01231 0.00512 -0.0880 0.0525 0.6681 5.500 0.9243 0.01253 0.00534 -0.0879 0.0502 0.6699 5.750 0.9517 0.01278 0.00557 -0.0878 0.0480 0.6717 6.000 0.9794 0.01300 0.00580 -0.0877 0.0464 0.6733 6.250 1.0067 0.01324 0.00603 -0.0875 0.0445 0.6750 6.500 1.0337 0.01351 0.00629 -0.0873 0.0426 0.6767 6.750 1.0608 0.01376 0.00655 -0.0871 0.0413 0.6784 7.000 1.0878 0.01402 0.00681 -0.0868 0.0400 0.6800 7.500 1.1408 0.01460 0.00739 -0.0862 0.0372 0.6835 7.750 1.1673 0.01488 0.00769 -0.0859 0.0362 0.6853 8.000 1.1935 0.01516 0.00800 -0.0856 0.0350 0.6870 8.250 1.2194 0.01547 0.00831 -0.0852 0.0338 0.6888 8.500 1.2448 0.01582 0.00866 -0.0847 0.0327 0.6907 8.750 1.2702 0.01615 0.00902 -0.0842 0.0319 0.6925 9.000 1.2956 0.01648 0.00937 -0.0837 0.0311 0.6944 9.250 1.3205 0.01683 0.00974 -0.0832 0.0303 0.6961 9.500 1.3451 0.01719 0.01011 -0.0826 0.0295 0.6978 9.750 1.3692 0.01759 0.01052 -0.0819 0.0287 0.6992 10.000 1.3927 0.01804 0.01097 -0.0811 0.0279 0.7007 10.250 1.4167 0.01840 0.01139 -0.0804 0.0274 0.7029 10.500 1.4401 0.01879 0.01182 -0.0797 0.0268 0.7051 10.750 1.4630 0.01921 0.01228 -0.0788 0.0262 0.7072 11.000 1.4853 0.01966 0.01276 -0.0779 0.0257 0.7094 11.250 1.5070 0.02013 0.01326 -0.0769 0.0252 0.7114 11.500 1.5280 0.02065 0.01380 -0.0758 0.0247 0.7134 11.750 1.5478 0.02122 0.01441 -0.0745 0.0242 0.7153 12.000 1.5678 0.02173 0.01496 -0.0732 0.0239 0.7171 12.250 1.5870 0.02224 0.01552 -0.0718 0.0236 0.7187 12.500 1.6050 0.02278 0.01612 -0.0702 0.0233 0.7206 12.750 1.6216 0.02334 0.01675 -0.0684 0.0230 0.7227 13.000 1.6349 0.02392 0.01739 -0.0660 0.0227 0.7249 13.250 1.6478 0.02457 0.01810 -0.0637 0.0224 0.7271 13.500 1.6613 0.02529 0.01887 -0.0616 0.0221 0.7293 13.750 1.6744 0.02605 0.01969 -0.0595 0.0218 0.7316 14.000 1.6868 0.02689 0.02058 -0.0575 0.0215 0.7338 14.250 1.6982 0.02782 0.02156 -0.0554 0.0212 0.7360 14.500 1.7083 0.02887 0.02266 -0.0533 0.0209 0.7378 14.750 1.7172 0.03002 0.02389 -0.0512 0.0205 0.7401 15.000 1.7276 0.03108 0.02504 -0.0494 0.0204 0.7427 15.250 1.7375 0.03223 0.02628 -0.0477 0.0203 0.7454 15.500 1.7462 0.03349 0.02763 -0.0460 0.0201 0.7481 15.750 1.7541 0.03488 0.02910 -0.0443 0.0199 0.7506 16.000 1.7611 0.03638 0.03068 -0.0428 0.0198 0.7529 16.250 1.7670 0.03802 0.03240 -0.0413 0.0196 0.7549 16.500 1.7721 0.03979 0.03427 -0.0400 0.0194 0.7569 16.750 1.7760 0.04174 0.03632 -0.0388 0.0193 0.7592 17.000 1.7786 0.04389 0.03857 -0.0378 0.0191 0.7615 17.250 1.7797 0.04625 0.04103 -0.0369 0.0190 0.7638 17.500 1.7794 0.04888 0.04376 -0.0363 0.0188 0.7661 17.750 1.7776 0.05177 0.04675 -0.0358 0.0187 0.7684 18.000 1.7736 0.05504 0.05013 -0.0357 0.0186 0.7705 18.250 1.7678 0.05871 0.05391 -0.0359 0.0184 0.7724 18.500 1.7596 0.06291 0.05824 -0.0367 0.0183 0.7743 18.750 1.7487 0.06773 0.06319 -0.0380 0.0182 0.7764 19.000 1.7340 0.07336 0.06897 -0.0399 0.0181 0.7784 19.250 1.7147 0.08009 0.07586 -0.0428 0.0181 0.7802