XFOIL Version 6.96 Calculated polar for: NACA 2415 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.5299 0.10111 0.09265 -0.0426 1.0000 0.0950 -11.500 -0.5757 0.08737 0.07895 -0.0507 1.0000 0.0956 -11.250 -0.6504 0.07155 0.06303 -0.0613 1.0000 0.0950 -11.000 -0.7021 0.06391 0.05524 -0.0638 1.0000 0.0945 -10.750 -0.7402 0.05964 0.05082 -0.0612 1.0000 0.0947 -10.500 -0.7675 0.05593 0.04687 -0.0581 1.0000 0.0954 -10.250 -0.7877 0.05253 0.04315 -0.0548 1.0000 0.0965 -10.000 -0.7939 0.04990 0.04030 -0.0519 1.0000 0.0980 -9.750 -0.7861 0.04835 0.03875 -0.0499 1.0000 0.0997 -9.500 -0.7809 0.04668 0.03698 -0.0475 1.0000 0.1020 -9.250 -0.7778 0.04478 0.03489 -0.0450 1.0000 0.1048 -9.000 -0.7757 0.04260 0.03235 -0.0423 1.0000 0.1080 -8.750 -0.7662 0.04109 0.03076 -0.0402 1.0000 0.1110 -8.500 -0.7544 0.03992 0.02959 -0.0382 1.0000 0.1144 -8.250 -0.7442 0.03848 0.02794 -0.0360 1.0000 0.1189 -8.000 -0.7328 0.03703 0.02630 -0.0340 1.0000 0.1236 -7.750 -0.7189 0.03610 0.02541 -0.0322 1.0000 0.1282 -7.500 -0.7058 0.03490 0.02396 -0.0303 1.0000 0.1347 -7.250 -0.6911 0.03398 0.02309 -0.0286 1.0000 0.1405 -7.000 -0.6762 0.03305 0.02203 -0.0269 1.0000 0.1480 -6.750 -0.6607 0.03222 0.02122 -0.0253 1.0000 0.1555 -6.500 -0.6446 0.03141 0.02026 -0.0238 1.0000 0.1648 -6.250 -0.6283 0.03076 0.01970 -0.0223 1.0000 0.1736 -6.000 -0.6112 0.03009 0.01894 -0.0209 1.0000 0.1842 -5.750 -0.5939 0.02954 0.01837 -0.0197 1.0000 0.1958 -5.500 -0.5762 0.02904 0.01794 -0.0184 1.0000 0.2074 -5.250 -0.5543 0.02857 0.01745 -0.0180 0.9986 0.2215 -5.000 -0.5169 0.02811 0.01700 -0.0205 0.9915 0.2408 -4.750 -0.4798 0.02768 0.01655 -0.0229 0.9838 0.2620 -4.500 -0.4438 0.02727 0.01610 -0.0250 0.9757 0.2849 -4.250 -0.4057 0.02689 0.01583 -0.0275 0.9683 0.3084 -4.000 -0.3718 0.02652 0.01550 -0.0291 0.9590 0.3338 -3.750 -0.3362 0.02617 0.01522 -0.0310 0.9504 0.3615 -3.500 -0.3002 0.02585 0.01498 -0.0328 0.9417 0.3918 -3.250 -0.2688 0.02554 0.01481 -0.0337 0.9316 0.4225 -3.000 -0.2311 0.02525 0.01466 -0.0357 0.9237 0.4594 -2.750 -0.2028 0.02501 0.01457 -0.0357 0.9124 0.4958 -2.500 -0.1671 0.02478 0.01450 -0.0370 0.9040 0.5395 -2.250 -0.1375 0.02458 0.01446 -0.0370 0.8930 0.5835 -2.000 -0.1069 0.02442 0.01446 -0.0370 0.8829 0.6295 -1.750 -0.0727 0.02425 0.01444 -0.0374 0.8739 0.6785 -1.500 -0.0446 0.02419 0.01453 -0.0365 0.8627 0.7234 -1.250 -0.0066 0.02409 0.01450 -0.0371 0.8548 0.7705 -1.000 0.0242 0.02415 0.01462 -0.0366 0.8427 0.8119 -0.750 0.0725 0.02408 0.01452 -0.0392 0.8359 0.8517 -0.500 0.1115 0.02419 0.01458 -0.0407 0.8233 0.8867 -0.250 0.1646 0.02415 0.01446 -0.0448 0.8143 0.9167 0.000 0.2198 0.02409 0.01433 -0.0495 0.8037 0.9421 0.250 0.2784 0.02399 0.01415 -0.0552 0.7925 0.9646 0.500 0.3419 0.02369 0.01375 -0.0618 0.7827 0.9844 0.750 0.3909 0.02355 0.01355 -0.0662 0.7686 1.0000 1.000 0.4093 0.02349 0.01342 -0.0648 0.7545 1.0000 1.250 0.4315 0.02340 0.01323 -0.0638 0.7420 1.0000 1.500 0.4525 0.02338 0.01314 -0.0626 0.7288 1.0000 1.750 0.4701 0.02351 0.01321 -0.0609 0.7145 1.0000 2.000 0.4906 0.02361 0.01324 -0.0596 0.7016 1.0000 2.250 0.5169 0.02356 0.01310 -0.0590 0.6906 1.0000 2.500 0.5345 0.02381 0.01332 -0.0572 0.6763 1.0000 2.750 0.5544 0.02403 0.01350 -0.0558 0.6632 1.0000 3.000 0.5785 0.02414 0.01354 -0.0548 0.6513 1.0000 3.250 0.6012 0.02429 0.01365 -0.0536 0.6383 1.0000 3.500 0.6204 0.02456 0.01390 -0.0520 0.6239 1.0000 3.750 0.6418 0.02477 0.01407 -0.0505 0.6100 1.0000 4.000 0.6656 0.02492 0.01417 -0.0495 0.5968 1.0000 4.250 0.6891 0.02510 0.01432 -0.0483 0.5835 1.0000 4.500 0.7083 0.02548 0.01471 -0.0468 0.5694 1.0000 4.750 0.7298 0.02581 0.01505 -0.0455 0.5562 1.0000 5.000 0.7545 0.02604 0.01524 -0.0446 0.5439 1.0000 5.250 0.7757 0.02641 0.01562 -0.0433 0.5304 1.0000 5.500 0.7952 0.02685 0.01610 -0.0418 0.5165 1.0000 5.750 0.8167 0.02723 0.01649 -0.0405 0.5030 1.0000 6.000 0.8399 0.02752 0.01676 -0.0394 0.4895 1.0000 6.250 0.8610 0.02787 0.01712 -0.0381 0.4749 1.0000 6.500 0.8788 0.02833 0.01762 -0.0363 0.4592 1.0000 6.750 0.8967 0.02878 0.01809 -0.0346 0.4432 1.0000 7.000 0.9144 0.02923 0.01856 -0.0328 0.4271 1.0000 7.250 0.9318 0.02970 0.01906 -0.0310 0.4110 1.0000 7.500 0.9487 0.03020 0.01958 -0.0292 0.3949 1.0000 7.750 0.9650 0.03074 0.02013 -0.0273 0.3788 1.0000 8.000 0.9803 0.03131 0.02072 -0.0253 0.3625 1.0000 8.250 0.9946 0.03194 0.02135 -0.0233 0.3462 1.0000 8.500 1.0074 0.03262 0.02203 -0.0211 0.3298 1.0000 8.750 1.0188 0.03338 0.02278 -0.0188 0.3133 1.0000 9.000 1.0284 0.03421 0.02361 -0.0164 0.2970 1.0000 9.250 1.0353 0.03510 0.02447 -0.0137 0.2814 1.0000 9.500 1.0413 0.03610 0.02545 -0.0110 0.2662 1.0000 9.750 1.0461 0.03729 0.02665 -0.0084 0.2512 1.0000 10.000 1.0507 0.03862 0.02797 -0.0062 0.2368 1.0000 10.250 1.0552 0.04007 0.02944 -0.0041 0.2232 1.0000 10.500 1.0598 0.04164 0.03099 -0.0022 0.2107 1.0000 10.750 1.0644 0.04326 0.03254 -0.0005 0.1992 1.0000 11.000 1.0681 0.04506 0.03437 0.0011 0.1881 1.0000 11.250 1.0709 0.04709 0.03648 0.0024 0.1777 1.0000 11.500 1.0752 0.04899 0.03833 0.0036 0.1689 1.0000 11.750 1.0773 0.05123 0.04068 0.0046 0.1601 1.0000 12.000 1.0805 0.05344 0.04292 0.0055 0.1526 1.0000 12.250 1.0833 0.05577 0.04531 0.0063 0.1456 1.0000 12.500 1.0870 0.05808 0.04765 0.0070 0.1396 1.0000 12.750 1.0875 0.06085 0.05056 0.0074 0.1337 1.0000 13.000 1.0965 0.06258 0.05219 0.0081 0.1287 1.0000 13.250 1.0917 0.06625 0.05614 0.0081 0.1242 1.0000 13.500 1.0912 0.06933 0.05935 0.0081 0.1200 1.0000 13.750 1.1022 0.07095 0.06087 0.0088 0.1160 1.0000 14.000 1.0923 0.07551 0.06571 0.0081 0.1131 1.0000 14.250 1.0800 0.08051 0.07097 0.0069 0.1105 1.0000 14.500 1.0696 0.08537 0.07602 0.0057 0.1080 1.0000 14.750 1.0689 0.08881 0.07951 0.0051 0.1054 1.0000 15.000 1.0725 0.09169 0.08241 0.0048 0.1029 1.0000 15.250 1.0303 0.10235 0.09342 -0.0003 0.1020 1.0000 15.500 0.9167 0.13018 0.12167 -0.0163 0.1015 1.0000