XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY NLF(1)-0416 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 ------ -------- --------- --------- -------- -------- -------- -16.750 -0.6781 0.12034 0.11728 -0.0345 1.0000 0.0076 -16.250 -0.7310 0.10049 0.09710 -0.0449 1.0000 0.0075 -16.000 -0.7532 0.09220 0.08868 -0.0493 1.0000 0.0075 -15.750 -0.7699 0.08511 0.08146 -0.0532 1.0000 0.0075 -15.500 -0.7871 0.07824 0.07444 -0.0570 1.0000 0.0075 -15.000 -0.8115 0.06691 0.06283 -0.0631 1.0000 0.0075 -14.750 -0.8213 0.06209 0.05789 -0.0653 1.0000 0.0075 -14.250 -0.8395 0.05345 0.04898 -0.0688 1.0000 0.0076 -14.000 -0.8441 0.05017 0.04558 -0.0696 1.0000 0.0076 -13.750 -0.8499 0.04701 0.04232 -0.0700 1.0000 0.0076 -13.500 -0.8551 0.04414 0.03934 -0.0701 1.0000 0.0077 -13.250 -0.8586 0.04161 0.03672 -0.0698 1.0000 0.0078 -13.000 -0.8604 0.03939 0.03441 -0.0691 1.0000 0.0078 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0.4487 0.6730 2.000 0.6618 0.01031 0.00365 -0.0967 0.4441 0.6749 2.500 0.7187 0.01047 0.00379 -0.0970 0.4353 0.6786 2.750 0.7473 0.01056 0.00385 -0.0972 0.4303 0.6805 3.000 0.7753 0.01065 0.00393 -0.0972 0.4255 0.6820 3.250 0.8031 0.01073 0.00402 -0.0972 0.4209 0.6833 3.500 0.8312 0.01080 0.00412 -0.0972 0.4156 0.6845 3.750 0.8587 0.01090 0.00422 -0.0972 0.4099 0.6857 4.000 0.8864 0.01100 0.00433 -0.0972 0.4043 0.6868 4.250 0.9142 0.01109 0.00443 -0.0972 0.3976 0.6877 4.500 0.9412 0.01122 0.00454 -0.0971 0.3905 0.6887 4.750 0.9689 0.01131 0.00466 -0.0971 0.3829 0.6899 5.000 0.9956 0.01146 0.00479 -0.0970 0.3749 0.6910 5.250 1.0229 0.01158 0.00492 -0.0969 0.3659 0.6920 5.500 1.0494 0.01174 0.00507 -0.0968 0.3564 0.6929 5.750 1.0757 0.01192 0.00523 -0.0966 0.3453 0.6938 6.000 1.1017 0.01212 0.00540 -0.0963 0.3338 0.6947 6.250 1.1272 0.01235 0.00561 -0.0960 0.3218 0.6956 6.500 1.1521 0.01263 0.00584 -0.0956 0.3088 0.6965 6.750 1.1766 0.01293 0.00609 -0.0952 0.2959 0.6975 7.000 1.2005 0.01324 0.00638 -0.0946 0.2821 0.6985 7.250 1.2244 0.01355 0.00666 -0.0941 0.2691 0.6993 7.500 1.2479 0.01387 0.00697 -0.0935 0.2570 0.7002 7.750 1.2708 0.01423 0.00732 -0.0928 0.2449 0.7010 8.000 1.2930 0.01462 0.00768 -0.0920 0.2325 0.7018 8.500 1.3366 0.01541 0.00845 -0.0903 0.2092 0.7036 8.750 1.3575 0.01584 0.00886 -0.0893 0.1985 0.7046 9.000 1.3773 0.01630 0.00930 -0.0882 0.1878 0.7056 9.250 1.3964 0.01678 0.00977 -0.0870 0.1770 0.7066 9.500 1.4152 0.01725 0.01024 -0.0857 0.1672 0.7076 9.750 1.4311 0.01775 0.01073 -0.0839 0.1581 0.7087 10.000 1.4454 0.01828 0.01125 -0.0818 0.1490 0.7098 10.250 1.4603 0.01882 0.01181 -0.0799 0.1411 0.7110 10.500 1.4727 0.01948 0.01246 -0.0777 0.1330 0.7123 10.750 1.4863 0.02009 0.01309 -0.0758 0.1254 0.7135 11.000 1.4972 0.02084 0.01384 -0.0735 0.1179 0.7146 11.250 1.5071 0.02164 0.01466 -0.0713 0.1098 0.7157 11.500 1.5159 0.02253 0.01556 -0.0690 0.1021 0.7167 11.750 1.5216 0.02363 0.01666 -0.0665 0.0942 0.7179 12.000 1.5284 0.02472 0.01778 -0.0644 0.0873 0.7190 12.250 1.5332 0.02601 0.01910 -0.0623 0.0816 0.7203 12.500 1.5388 0.02733 0.02048 -0.0605 0.0767 0.7216 12.750 1.5414 0.02898 0.02216 -0.0587 0.0721 0.7229 13.000 1.5462 0.03059 0.02383 -0.0573 0.0681 0.7242 13.250 1.5476 0.03260 0.02589 -0.0561 0.0641 0.7256 13.500 1.5496 0.03471 0.02807 -0.0552 0.0607 0.7269 13.750 1.5511 0.03700 0.03042 -0.0545 0.0571 0.7282 14.000 1.5496 0.03971 0.03318 -0.0540 0.0539 0.7295 14.500 1.5497 0.04519 0.03883 -0.0536 0.0484 0.7320 14.750 1.5463 0.04846 0.04217 -0.0537 0.0459 0.7333 15.000 1.5453 0.05155 0.04536 -0.0540 0.0436 0.7346 15.250 1.5421 0.05497 0.04886 -0.0544 0.0412 0.7361 15.500 1.5367 0.05876 0.05272 -0.0549 0.0389 0.7376 15.750 1.5339 0.06233 0.05638 -0.0556 0.0369 0.7392 16.000 1.5296 0.06617 0.06031 -0.0564 0.0348 0.7408 16.250 1.5237 0.07035 0.06457 -0.0575 0.0330 0.7424 16.500 1.5195 0.07439 0.06870 -0.0586 0.0312 0.7440 16.750 1.5152 0.07854 0.07293 -0.0598 0.0296 0.7454 17.250 1.5041 0.08747 0.08204 -0.0627 0.0266 0.7482 17.500 1.4993 0.09198 0.08666 -0.0643 0.0252 0.7497 17.750 1.4928 0.09681 0.09157 -0.0662 0.0238 0.7512 18.000 1.4861 0.10177 0.09663 -0.0682 0.0225 0.7528 18.250 1.4815 0.10644 0.10140 -0.0701 0.0213 0.7546 18.500 1.4752 0.11149 0.10654 -0.0723 0.0201 0.7564 18.750 1.4675 0.11683 0.11198 -0.0748 0.0191 0.7581