XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY LS(1)-0421MOD 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -1.0285 0.09708 0.09211 -0.0449 1.0000 0.0235 -19.500 -1.0341 0.09254 0.08748 -0.0470 1.0000 0.0237 -19.250 -1.0389 0.08814 0.08299 -0.0491 1.0000 0.0239 -19.000 -1.0429 0.08390 0.07866 -0.0511 1.0000 0.0241 -18.750 -1.0461 0.07985 0.07453 -0.0529 1.0000 0.0242 -18.500 -1.0482 0.07603 0.07062 -0.0545 1.0000 0.0244 -18.250 -1.0490 0.07242 0.06692 -0.0560 1.0000 0.0246 -18.000 -1.0488 0.06900 0.06342 -0.0574 1.0000 0.0248 -17.750 -1.0478 0.06576 0.06010 -0.0586 1.0000 0.0250 -17.500 -1.0459 0.06269 0.05695 -0.0597 1.0000 0.0252 -17.250 -1.0433 0.05976 0.05394 -0.0607 1.0000 0.0253 -17.000 -1.0424 0.05671 0.05084 -0.0616 1.0000 0.0255 -16.750 -1.0398 0.05392 0.04800 -0.0624 1.0000 0.0258 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0.2974 0.00973 0.00369 -0.0873 0.5470 0.6156 -1.500 0.3291 0.00981 0.00371 -0.0880 0.5390 0.6226 -1.250 0.3596 0.00993 0.00379 -0.0885 0.5306 0.6293 -1.000 0.3907 0.01000 0.00387 -0.0890 0.5231 0.6352 -0.750 0.4218 0.01009 0.00391 -0.0896 0.5152 0.6393 -0.500 0.4529 0.01018 0.00394 -0.0902 0.5082 0.6425 -0.250 0.4843 0.01025 0.00397 -0.0909 0.5006 0.6456 0.000 0.5143 0.01035 0.00405 -0.0913 0.4926 0.6489 0.250 0.5446 0.01046 0.00415 -0.0917 0.4853 0.6527 0.500 0.5751 0.01057 0.00423 -0.0921 0.4767 0.6564 0.750 0.6052 0.01071 0.00431 -0.0926 0.4671 0.6597 1.000 0.6356 0.01083 0.00438 -0.0931 0.4552 0.6625 1.250 0.6658 0.01098 0.00445 -0.0936 0.4442 0.6649 1.500 0.6958 0.01111 0.00453 -0.0941 0.4339 0.6670 1.750 0.7250 0.01124 0.00465 -0.0943 0.4248 0.6693 2.000 0.7543 0.01139 0.00477 -0.0946 0.4146 0.6715 2.250 0.7834 0.01156 0.00490 -0.0949 0.4046 0.6738 2.500 0.8123 0.01175 0.00504 -0.0952 0.3937 0.6763 2.750 0.8414 0.01193 0.00518 -0.0955 0.3840 0.6788 3.000 0.8701 0.01213 0.00533 -0.0957 0.3737 0.6813 3.250 0.8990 0.01232 0.00548 -0.0960 0.3645 0.6838 3.500 0.9273 0.01255 0.00565 -0.0962 0.3539 0.6860 3.750 0.9558 0.01275 0.00581 -0.0965 0.3445 0.6878 4.000 0.9830 0.01299 0.00602 -0.0964 0.3338 0.6898 4.250 1.0104 0.01321 0.00623 -0.0965 0.3227 0.6919 4.500 1.0367 0.01350 0.00647 -0.0963 0.3106 0.6941 4.750 1.0628 0.01380 0.00673 -0.0961 0.2977 0.6965 5.000 1.0886 0.01412 0.00699 -0.0960 0.2849 0.6987 5.250 1.1136 0.01447 0.00728 -0.0956 0.2722 0.7009 5.500 1.1378 0.01487 0.00760 -0.0952 0.2597 0.7031 5.750 1.1623 0.01523 0.00792 -0.0948 0.2479 0.7053 6.000 1.1858 0.01563 0.00826 -0.0943 0.2366 0.7073 6.250 1.2082 0.01608 0.00864 -0.0936 0.2253 0.7092 6.500 1.2297 0.01650 0.00903 -0.0928 0.2143 0.7113 6.750 1.2503 0.01694 0.00945 -0.0917 0.2047 0.7134 7.000 1.2687 0.01745 0.00993 -0.0904 0.1953 0.7155 7.250 1.2872 0.01791 0.01039 -0.0890 0.1870 0.7179 7.500 1.2996 0.01845 0.01091 -0.0866 0.1800 0.7205 7.750 1.3153 0.01901 0.01146 -0.0849 0.1732 0.7232 8.000 1.3307 0.01970 0.01213 -0.0833 0.1671 0.7257 8.250 1.3481 0.02032 0.01276 -0.0821 0.1619 0.7280 8.500 1.3635 0.02108 0.01350 -0.0808 0.1568 0.7301 8.750 1.3792 0.02184 0.01427 -0.0796 0.1528 0.7322 9.000 1.3952 0.02259 0.01507 -0.0784 0.1489 0.7345 9.250 1.4094 0.02349 0.01599 -0.0772 0.1449 0.7367 9.500 1.4229 0.02448 0.01700 -0.0760 0.1413 0.7390 9.750 1.4382 0.02539 0.01795 -0.0751 0.1380 0.7415 10.000 1.4518 0.02644 0.01904 -0.0741 0.1346 0.7439 10.250 1.4638 0.02765 0.02026 -0.0730 0.1315 0.7464 10.500 1.4769 0.02882 0.02147 -0.0722 0.1290 0.7489 10.750 1.4902 0.03002 0.02270 -0.0714 0.1264 0.7513 11.000 1.5018 0.03134 0.02406 -0.0706 0.1238 0.7537 11.250 1.5117 0.03282 0.02559 -0.0697 0.1213 0.7562 11.500 1.5206 0.03442 0.02724 -0.0688 0.1191 0.7588 11.750 1.5317 0.03586 0.02875 -0.0681 0.1170 0.7613 12.000 1.5411 0.03747 0.03041 -0.0674 0.1148 0.7639 12.250 1.5487 0.03929 0.03227 -0.0667 0.1126 0.7664 12.500 1.5547 0.04128 0.03429 -0.0661 0.1105 0.7689 12.750 1.5615 0.04324 0.03630 -0.0655 0.1088 0.7714 13.250 1.5759 0.04716 0.04036 -0.0646 0.1054 0.7759 13.500 1.5809 0.04940 0.04267 -0.0641 0.1038 0.7785 13.750 1.5846 0.05183 0.04516 -0.0638 0.1021 0.7813 14.000 1.5869 0.05443 0.04781 -0.0635 0.1006 0.7841 14.250 1.5912 0.05688 0.05034 -0.0633 0.0993 0.7870 14.500 1.5963 0.05928 0.05281 -0.0632 0.0980 0.7898 14.750 1.6003 0.06185 0.05544 -0.0631 0.0966 0.7923 15.000 1.6025 0.06464 0.05830 -0.0632 0.0951 0.7946 15.250 1.6036 0.06752 0.06125 -0.0632 0.0937 0.7969 15.500 1.6024 0.07076 0.06455 -0.0633 0.0923 0.7995 15.750 1.6023 0.07386 0.06773 -0.0634 0.0911 0.8022 16.000 1.6051 0.07667 0.07063 -0.0636 0.0900 0.8051 16.250 1.6065 0.07966 0.07371 -0.0639 0.0888 0.8079 16.500 1.6071 0.08278 0.07689 -0.0643 0.0876 0.8105 16.750 1.6062 0.08613 0.08030 -0.0648 0.0865 0.8129 17.000 1.6050 0.08949 0.08373 -0.0653 0.0854 0.8150 17.250 1.6015 0.09319 0.08751 -0.0659 0.0844 0.8173