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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.750 -0.4620 0.13187 0.12596 -0.0313 1.0000 0.0373 -13.500 -0.4705 0.12472 0.11883 -0.0347 1.0000 0.0378 -13.250 -0.6861 0.07375 0.06701 -0.0669 1.0000 0.0349 -12.750 -0.7251 0.06399 0.05689 -0.0704 1.0000 0.0351 -12.500 -0.7327 0.06088 0.05369 -0.0706 1.0000 0.0353 -12.250 -0.7408 0.05798 0.05069 -0.0704 1.0000 0.0356 -12.000 -0.7500 0.05525 0.04783 -0.0696 1.0000 0.0359 -11.750 -0.7598 0.05278 0.04523 -0.0681 1.0000 0.0362 -11.500 -0.7709 0.05061 0.04293 -0.0657 1.0000 0.0364 -11.250 -0.7841 0.04877 0.04097 -0.0624 1.0000 0.0367 -11.000 -0.7946 0.04701 0.03907 -0.0591 1.0000 0.0369 -10.750 -0.8008 0.04526 0.03716 -0.0561 1.0000 0.0372 -10.500 -0.8048 0.04364 0.03537 -0.0529 1.0000 0.0376 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0.9255 0.1002 -5.500 -0.3012 0.02183 0.01282 -0.0640 0.9195 0.1284 -5.250 -0.2642 0.02080 0.01210 -0.0665 0.9151 0.1783 -5.000 -0.2397 0.01993 0.01162 -0.0668 0.9057 0.2446 -4.750 -0.2059 0.01882 0.01105 -0.0690 0.8996 0.3476 -4.500 -0.1737 0.01810 0.01099 -0.0699 0.8942 0.4599 -4.250 -0.1540 0.01849 0.01182 -0.0667 0.8840 0.5364 -4.000 -0.1198 0.01872 0.01204 -0.0669 0.8770 0.5894 -3.750 -0.0924 0.01905 0.01231 -0.0659 0.8674 0.6161 -3.500 -0.0610 0.01924 0.01239 -0.0656 0.8575 0.6363 -3.250 -0.0308 0.01935 0.01237 -0.0654 0.8466 0.6532 -3.000 -0.0048 0.01970 0.01267 -0.0637 0.8358 0.6653 -2.750 0.0218 0.01998 0.01287 -0.0623 0.8254 0.6781 -2.500 0.0486 0.02018 0.01299 -0.0611 0.8133 0.6904 -2.250 0.0745 0.02027 0.01302 -0.0599 0.8004 0.6985 -2.000 0.1016 0.02029 0.01295 -0.0587 0.7870 0.7044 -1.750 0.1297 0.02017 0.01272 -0.0587 0.7695 0.7129 -1.500 0.1564 0.02009 0.01255 -0.0580 0.7506 0.7190 -1.250 0.1800 0.02011 0.01250 -0.0562 0.7282 0.7238 -1.000 0.2062 0.02004 0.01231 -0.0554 0.6994 0.7302 -0.750 0.2373 0.01986 0.01192 -0.0561 0.6555 0.7384 -0.500 0.2598 0.01993 0.01169 -0.0540 0.5962 0.7421 -0.250 0.2822 0.02017 0.01151 -0.0523 0.5425 0.7466 0.000 0.3065 0.02043 0.01144 -0.0515 0.5083 0.7519 0.250 0.3355 0.02064 0.01136 -0.0522 0.4848 0.7578 0.500 0.3613 0.02081 0.01137 -0.0519 0.4678 0.7615 0.750 0.3857 0.02100 0.01144 -0.0510 0.4546 0.7646 1.000 0.4114 0.02120 0.01149 -0.0506 0.4429 0.7683 1.250 0.4394 0.02135 0.01154 -0.0508 0.4326 0.7720 1.500 0.4691 0.02151 0.01158 -0.0516 0.4228 0.7759 1.750 0.5014 0.02170 0.01162 -0.0530 0.4143 0.7798 2.000 0.5280 0.02182 0.01172 -0.0528 0.4061 0.7819 2.250 0.5541 0.02200 0.01183 -0.0525 0.3987 0.7844 2.500 0.5813 0.02223 0.01195 -0.0525 0.3921 0.7871 2.750 0.6095 0.02238 0.01212 -0.0528 0.3850 0.7899 3.000 0.6387 0.02257 0.01226 -0.0534 0.3782 0.7924 3.250 0.6686 0.02285 0.01242 -0.0541 0.3723 0.7955 3.500 0.6998 0.02307 0.01265 -0.0553 0.3658 0.7988 3.750 0.7274 0.02327 0.01287 -0.0555 0.3596 0.8011 4.000 0.7539 0.02349 0.01307 -0.0554 0.3541 0.8031 4.250 0.7813 0.02380 0.01329 -0.0555 0.3491 0.8052 4.500 0.8083 0.02402 0.01360 -0.0556 0.3433 0.8076 4.750 0.8356 0.02428 0.01389 -0.0558 0.3376 0.8105 5.000 0.8639 0.02458 0.01415 -0.0562 0.3325 0.8136 5.250 0.8935 0.02494 0.01447 -0.0570 0.3278 0.8166 5.500 0.9218 0.02525 0.01488 -0.0575 0.3221 0.8191 5.750 0.9467 0.02553 0.01521 -0.0572 0.3169 0.8211 6.000 0.9723 0.02582 0.01550 -0.0570 0.3123 0.8234 6.250 0.9985 0.02620 0.01586 -0.0570 0.3080 0.8259 6.500 1.0237 0.02656 0.01637 -0.0569 0.3025 0.8289 6.750 1.0500 0.02693 0.01679 -0.0570 0.2974 0.8322 7.000 1.0777 0.02731 0.01715 -0.0575 0.2929 0.8356 7.250 1.1025 0.02772 0.01761 -0.0573 0.2884 0.8383 7.500 1.1250 0.02813 0.01817 -0.0567 0.2832 0.8410 7.750 1.1485 0.02851 0.01861 -0.0563 0.2783 0.8438 8.000 1.1733 0.02889 0.01899 -0.0562 0.2742 0.8469 8.250 1.1971 0.02941 0.01961 -0.0560 0.2694 0.8502 8.500 1.2208 0.02994 0.02027 -0.0559 0.2641 0.8536 8.750 1.2420 0.03034 0.02073 -0.0551 0.2596 0.8567 9.000 1.2640 0.03073 0.02109 -0.0544 0.2559 0.8604 9.250 1.2823 0.03136 0.02195 -0.0534 0.2507 0.8647 9.500 1.3027 0.03193 0.02263 -0.0528 0.2457 0.8691 9.750 1.3223 0.03236 0.02309 -0.0519 0.2416 0.8730 10.000 1.3394 0.03295 0.02377 -0.0506 0.2373 0.8771 10.250 1.3548 0.03366 0.02467 -0.0493 0.2323 0.8816 10.500 1.3722 0.03426 0.02534 -0.0484 0.2278 0.8863 10.750 1.3874 0.03471 0.02576 -0.0468 0.2244 0.8909 11.000 1.3942 0.03563 0.02694 -0.0443 0.2196 0.8965 11.250 1.4057 0.03646 0.02791 -0.0426 0.2151 0.9024 11.500 1.4168 0.03709 0.02858 -0.0407 0.2114 0.9090 11.750 1.4258 0.03810 0.02973 -0.0390 0.2073 0.9166 12.000 1.4301 0.03922 0.03105 -0.0367 0.2029 0.9254 12.250 1.4371 0.04017 0.03210 -0.0348 0.1991 0.9358 12.500 1.4460 0.04102 0.03296 -0.0332 0.1957 0.9501 12.750 1.4435 0.04270 0.03493 -0.0312 0.1914 1.0000 13.000 1.4510 0.04443 0.03678 -0.0308 0.1871 1.0000 13.250 1.4623 0.04584 0.03820 -0.0306 0.1835 1.0000 13.500 1.4621 0.04840 0.04097 -0.0302 0.1793 1.0000 13.750 1.4631 0.05088 0.04360 -0.0300 0.1752 1.0000 14.000 1.4689 0.05288 0.04564 -0.0299 0.1718 1.0000 14.250 1.4653 0.05598 0.04889 -0.0299 0.1682 1.0000 14.500 1.4562 0.05980 0.05292 -0.0303 0.1644 1.0000 14.750 1.4539 0.06293 0.05613 -0.0307 0.1610 1.0000 15.000 1.4525 0.06604 0.05929 -0.0312 0.1580 1.0000 15.250 1.4263 0.07266 0.06620 -0.0332 0.1546 1.0000 15.500 1.4086 0.07852 0.07222 -0.0353 0.1512 1.0000 15.750 1.4123 0.08133 0.07502 -0.0363 0.1482 1.0000 16.000 1.3612 0.09313 0.08714 -0.0418 0.1448 1.0000 16.250 1.2919 0.10884 0.10314 -0.0497 0.1403 1.0000 16.500 1.3257 0.10659 0.10080 -0.0482 0.1379 1.0000