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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.500 -0.7269 0.11013 0.10526 -0.0511 1.0000 0.0514 -17.250 -0.7755 0.09748 0.09239 -0.0587 1.0000 0.0509 -17.000 -0.8195 0.08694 0.08156 -0.0649 1.0000 0.0506 -16.750 -0.8553 0.07871 0.07306 -0.0691 1.0000 0.0504 -16.500 -0.8838 0.07217 0.06626 -0.0719 1.0000 0.0503 -16.250 -0.9069 0.06683 0.06066 -0.0737 1.0000 0.0504 -16.000 -0.9250 0.06234 0.05593 -0.0746 1.0000 0.0505 -15.750 -0.9390 0.05846 0.05181 -0.0751 1.0000 0.0506 -15.500 -0.9500 0.05505 0.04816 -0.0751 1.0000 0.0509 -15.250 -0.9593 0.05200 0.04486 -0.0748 1.0000 0.0512 -15.000 -0.9671 0.04930 0.04191 -0.0742 1.0000 0.0514 -14.750 -0.9469 0.04762 0.04027 -0.0739 1.0000 0.0521 -14.500 -0.9330 0.04613 0.03878 -0.0735 1.0000 0.0527 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0.01537 0.00968 -0.0743 0.7768 0.6046 -4.750 -0.1051 0.01590 0.01018 -0.0726 0.7700 0.6141 -4.500 -0.0754 0.01619 0.01044 -0.0726 0.7605 0.6271 -4.250 -0.0505 0.01680 0.01103 -0.0706 0.7527 0.6344 -4.000 -0.0192 0.01704 0.01114 -0.0711 0.7458 0.6464 -3.750 0.0044 0.01761 0.01175 -0.0690 0.7370 0.6505 -3.500 0.0304 0.01808 0.01217 -0.0674 0.7295 0.6563 -3.250 0.0624 0.01820 0.01216 -0.0683 0.7223 0.6673 -3.000 0.0851 0.01875 0.01274 -0.0660 0.7138 0.6705 -2.750 0.1104 0.01918 0.01312 -0.0643 0.7070 0.6744 -2.500 0.1375 0.01953 0.01341 -0.0635 0.7000 0.6807 -2.250 0.1671 0.01960 0.01344 -0.0639 0.6913 0.6896 -2.000 0.1897 0.02014 0.01393 -0.0613 0.6844 0.6929 -1.750 0.2132 0.02064 0.01441 -0.0592 0.6774 0.6968 -1.500 0.2420 0.02071 0.01446 -0.0594 0.6691 0.7043 -1.250 0.2735 0.02055 0.01417 -0.0605 0.6621 0.7113 -1.000 0.2968 0.02082 0.01443 -0.0587 0.6547 0.7138 -0.750 0.3213 0.02097 0.01458 -0.0574 0.6464 0.7168 -0.500 0.3492 0.02099 0.01451 -0.0571 0.6395 0.7210 -0.250 0.3858 0.02072 0.01417 -0.0602 0.6309 0.7295 0.000 0.4128 0.02063 0.01404 -0.0600 0.6226 0.7330 0.250 0.4368 0.02078 0.01409 -0.0583 0.6160 0.7354 0.500 0.4591 0.02094 0.01432 -0.0567 0.6075 0.7388 0.750 0.4860 0.02098 0.01432 -0.0563 0.5997 0.7434 1.000 0.5206 0.02086 0.01408 -0.0584 0.5924 0.7490 1.250 0.5534 0.02067 0.01389 -0.0603 0.5832 0.7539 1.500 0.5775 0.02067 0.01384 -0.0590 0.5760 0.7559 1.750 0.6023 0.02072 0.01389 -0.0583 0.5679 0.7581 2.000 0.6280 0.02072 0.01388 -0.0577 0.5591 0.7610 2.250 0.6573 0.02072 0.01376 -0.0581 0.5508 0.7646 2.500 0.6878 0.02061 0.01368 -0.0592 0.5401 0.7686 2.750 0.7280 0.02052 0.01341 -0.0627 0.5311 0.7730 3.000 0.7512 0.02047 0.01345 -0.0618 0.5217 0.7754 3.250 0.7747 0.02048 0.01342 -0.0607 0.5135 0.7775 3.500 0.7997 0.02053 0.01347 -0.0602 0.5048 0.7798 3.750 0.8261 0.02053 0.01347 -0.0601 0.4955 0.7825 4.000 0.8548 0.02059 0.01347 -0.0605 0.4868 0.7858 4.250 0.8850 0.02060 0.01350 -0.0615 0.4764 0.7896 4.500 0.9214 0.02067 0.01347 -0.0640 0.4670 0.7931 4.750 0.9453 0.02067 0.01352 -0.0635 0.4567 0.7954 5.000 0.9677 0.02078 0.01354 -0.0624 0.4481 0.7976 5.250 0.9890 0.02085 0.01371 -0.0612 0.4376 0.8002 5.500 1.0146 0.02100 0.01376 -0.0611 0.4281 0.8029 5.750 1.0397 0.02110 0.01394 -0.0610 0.4167 0.8058 6.000 1.0675 0.02129 0.01406 -0.0616 0.4060 0.8089 6.250 1.0975 0.02152 0.01426 -0.0630 0.3936 0.8126 6.500 1.1167 0.02169 0.01446 -0.0616 0.3824 0.8151 6.750 1.1342 0.02195 0.01464 -0.0599 0.3714 0.8176 7.000 1.1521 0.02220 0.01496 -0.0585 0.3591 0.8202 7.250 1.1705 0.02256 0.01528 -0.0574 0.3471 0.8231 7.500 1.1885 0.02298 0.01565 -0.0564 0.3343 0.8263 7.750 1.2061 0.02343 0.01612 -0.0555 0.3209 0.8297 8.000 1.2193 0.02397 0.01662 -0.0540 0.3085 0.8327 8.250 1.2266 0.02460 0.01720 -0.0511 0.2969 0.8354 8.500 1.2369 0.02532 0.01795 -0.0490 0.2845 0.8386 8.750 1.2481 0.02623 0.01882 -0.0475 0.2731 0.8423 9.000 1.2603 0.02730 0.01981 -0.0465 0.2620 0.8460 9.250 1.2765 0.02840 0.02092 -0.0464 0.2507 0.8493 9.500 1.2848 0.02952 0.02197 -0.0447 0.2420 0.8519 9.750 1.2943 0.03059 0.02310 -0.0433 0.2333 0.8547 10.000 1.3036 0.03185 0.02428 -0.0420 0.2258 0.8579 10.250 1.3156 0.03308 0.02558 -0.0414 0.2181 0.8612 10.500 1.3280 0.03449 0.02687 -0.0410 0.2114 0.8646 10.750 1.3401 0.03582 0.02831 -0.0406 0.2051 0.8677 11.000 1.3475 0.03711 0.02961 -0.0392 0.1997 0.8709 11.250 1.3577 0.03843 0.03088 -0.0382 0.1946 0.8746 11.500 1.3683 0.03990 0.03245 -0.0377 0.1895 0.8783 11.750 1.3807 0.04143 0.03397 -0.0377 0.1849 0.8817 12.000 1.3928 0.04266 0.03513 -0.0369 0.1806 0.8846 12.250 1.3996 0.04425 0.03686 -0.0361 0.1766 0.8879 12.500 1.4087 0.04582 0.03847 -0.0356 0.1727 0.8914 12.750 1.4220 0.04718 0.03976 -0.0353 0.1690 0.8949 13.000 1.4339 0.04875 0.04138 -0.0351 0.1655 0.8984 13.250 1.4391 0.05044 0.04319 -0.0342 0.1624 0.9021 13.500 1.4476 0.05204 0.04485 -0.0337 0.1593 0.9064 13.750 1.4609 0.05344 0.04621 -0.0336 0.1563 0.9105 14.000 1.4743 0.05467 0.04743 -0.0330 0.1533 0.9142 14.250 1.4764 0.05691 0.04983 -0.0326 0.1508 0.9181 14.500 1.4830 0.05891 0.05193 -0.0325 0.1480 0.9223 14.750 1.4932 0.06067 0.05371 -0.0326 0.1455 0.9264 15.000 1.5062 0.06161 0.05459 -0.0317 0.1431 0.9315 15.250 1.5158 0.06328 0.05632 -0.0313 0.1408 0.9369 15.500 1.5154 0.06599 0.05922 -0.0313 0.1389 0.9420 15.750 1.5175 0.06831 0.06166 -0.0310 0.1368 0.9479 16.000 1.5239 0.07036 0.06378 -0.0311 0.1348 0.9539 16.250 1.5325 0.07176 0.06519 -0.0306 0.1329 0.9619 16.500 1.5511 0.07206 0.06539 -0.0297 0.1309 0.9743 16.750 1.5496 0.07500 0.06850 -0.0302 0.1292 1.0000 17.000 1.5443 0.07911 0.07283 -0.0317 0.1276 1.0000 17.250 1.5433 0.08279 0.07667 -0.0332 0.1258 1.0000 17.500 1.5470 0.08590 0.07988 -0.0345 0.1241 1.0000 17.750 1.5568 0.08822 0.08223 -0.0355 0.1226 1.0000 18.000 1.5746 0.08949 0.08347 -0.0362 0.1210 1.0000 18.250 1.5964 0.09028 0.08419 -0.0362 0.1194 1.0000 18.500 1.5773 0.09624 0.09045 -0.0387 0.1184 1.0000 18.750 1.5580 0.10248 0.09695 -0.0415 0.1172 1.0000 19.000 1.5391 0.10887 0.10358 -0.0446 0.1159 1.0000