XFOIL Version 6.96 Calculated polar for: NACA 65(2)-415 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 ------ -------- --------- --------- -------- -------- -------- -12.000 -0.4497 0.09622 0.09092 -0.0627 1.0000 0.0367 -11.750 -0.4717 0.08626 0.08101 -0.0684 1.0000 0.0359 -11.500 -0.5099 0.07613 0.07085 -0.0746 1.0000 0.0351 -11.250 -0.5457 0.06961 0.06425 -0.0772 1.0000 0.0347 -11.000 -0.5793 0.06522 0.05980 -0.0770 1.0000 0.0344 -10.750 -0.6134 0.06262 0.05716 -0.0739 1.0000 0.0342 -10.500 -0.6390 0.05946 0.05385 -0.0728 0.9939 0.0340 -10.250 -0.6457 0.05522 0.04928 -0.0752 0.9803 0.0341 -10.000 -0.6396 0.05164 0.04540 -0.0772 0.9701 0.0349 -9.750 -0.6301 0.04812 0.04149 -0.0790 0.9620 0.0358 -9.500 -0.6208 0.04492 0.03786 -0.0795 0.9526 0.0368 -9.250 -0.6039 0.04161 0.03404 -0.0807 0.9467 0.0376 -9.000 -0.5905 0.03902 0.03100 -0.0801 0.9373 0.0381 -8.750 -0.5671 0.03651 0.02799 -0.0810 0.9321 0.0388 -8.500 -0.5478 0.03460 0.02587 -0.0807 0.9240 0.0400 -8.250 -0.5218 0.03309 0.02425 -0.0815 0.9185 0.0415 -8.000 -0.4942 0.03153 0.02248 -0.0822 0.9136 0.0428 -7.750 -0.4710 0.03014 0.02091 -0.0818 0.9063 0.0438 -7.500 -0.4414 0.02871 0.01928 -0.0824 0.9016 0.0451 -7.250 -0.4143 0.02761 0.01798 -0.0825 0.8960 0.0468 -7.000 -0.3900 0.02653 0.01685 -0.0822 0.8893 0.0488 -6.750 -0.3625 0.02552 0.01585 -0.0826 0.8847 0.0508 -6.500 -0.3400 0.02472 0.01501 -0.0819 0.8783 0.0525 -6.250 -0.3175 0.02396 0.01418 -0.0812 0.8719 0.0546 -6.000 -0.2920 0.02324 0.01334 -0.0811 0.8673 0.0573 -5.750 -0.2761 0.02260 0.01275 -0.0795 0.8595 0.0608 -5.500 -0.2543 0.02201 0.01211 -0.0788 0.8541 0.0654 -5.250 -0.2320 0.02138 0.01140 -0.0782 0.8493 0.0704 -5.000 -0.2145 0.02090 0.01090 -0.0768 0.8419 0.0783 -4.750 -0.1925 0.02024 0.01028 -0.0762 0.8370 0.0950 -4.500 -0.1749 0.01932 0.00969 -0.0752 0.8315 0.1489 -4.250 -0.1667 0.01774 0.00909 -0.0734 0.8246 0.3376 -4.000 -0.1495 0.01721 0.00945 -0.0712 0.8203 0.5381 -3.750 -0.1255 0.01739 0.00963 -0.0701 0.8157 0.5928 -3.500 -0.1053 0.01792 0.01021 -0.0678 0.8096 0.6419 -3.250 -0.0838 0.01884 0.01117 -0.0647 0.8054 0.6856 -3.000 -0.0583 0.01939 0.01167 -0.0628 0.8024 0.7055 -2.750 -0.0368 0.01942 0.01157 -0.0620 0.7963 0.7151 -2.500 -0.0116 0.01947 0.01153 -0.0613 0.7916 0.7199 -2.250 0.0164 0.01940 0.01133 -0.0614 0.7881 0.7250 -2.000 0.0448 0.01924 0.01102 -0.0619 0.7847 0.7314 -1.750 0.0659 0.01935 0.01109 -0.0610 0.7788 0.7355 -1.500 0.0920 0.01934 0.01101 -0.0608 0.7747 0.7396 -1.250 0.1209 0.01924 0.01080 -0.0612 0.7715 0.7446 -1.000 0.1479 0.01918 0.01065 -0.0615 0.7676 0.7499 -0.750 0.1692 0.01933 0.01080 -0.0605 0.7622 0.7536 -0.500 0.1956 0.01934 0.01076 -0.0605 0.7584 0.7579 -0.250 0.2250 0.01927 0.01062 -0.0611 0.7554 0.7632 0.000 0.2515 0.01929 0.01061 -0.0611 0.7518 0.7676 0.250 0.2717 0.01949 0.01084 -0.0600 0.7462 0.7716 0.500 0.2979 0.01955 0.01088 -0.0600 0.7425 0.7764 0.750 0.3279 0.01951 0.01081 -0.0608 0.7397 0.7822 1.000 0.3549 0.01955 0.01085 -0.0606 0.7367 0.7858 1.250 0.3725 0.01987 0.01124 -0.0593 0.7305 0.7906 1.500 0.3987 0.01997 0.01135 -0.0594 0.7268 0.7964 1.750 0.4270 0.01999 0.01139 -0.0596 0.7239 0.8011 2.000 0.4566 0.01997 0.01140 -0.0599 0.7216 0.8055 2.250 0.4710 0.02046 0.01197 -0.0583 0.7147 0.8119 2.500 0.4958 0.02059 0.01216 -0.0580 0.7107 0.8172 2.750 0.5234 0.02062 0.01225 -0.0579 0.7078 0.8223 3.000 0.5542 0.02062 0.01228 -0.0585 0.7054 0.8284 3.250 0.5644 0.02122 0.01302 -0.0562 0.6977 0.8349 3.500 0.5901 0.02132 0.01320 -0.0559 0.6938 0.8409 3.750 0.6214 0.02128 0.01323 -0.0566 0.6909 0.8474 4.000 0.6347 0.02172 0.01380 -0.0544 0.6839 0.8544 4.250 0.6592 0.02184 0.01402 -0.0540 0.6786 0.8623 4.500 0.6898 0.02166 0.01394 -0.0541 0.6751 0.8682 4.750 0.7034 0.02209 0.01451 -0.0521 0.6671 0.8774 5.000 0.7290 0.02200 0.01455 -0.0515 0.6616 0.8849 5.250 0.7591 0.02177 0.01443 -0.0515 0.6561 0.8935 5.500 0.7751 0.02182 0.01464 -0.0494 0.6463 0.9040 5.750 0.7992 0.02156 0.01453 -0.0483 0.6369 0.9142 6.000 0.8275 0.02084 0.01391 -0.0475 0.6226 0.9251 6.250 0.8529 0.01974 0.01282 -0.0456 0.5954 0.9377 6.500 0.8673 0.01941 0.01257 -0.0431 0.5601 0.9567 6.750 0.8894 0.01929 0.01250 -0.0424 0.5199 0.9912 7.000 0.9039 0.01940 0.01245 -0.0404 0.4669 1.0000 7.250 0.9102 0.02006 0.01248 -0.0371 0.3715 1.0000 7.500 0.9036 0.02173 0.01356 -0.0332 0.2891 1.0000 7.750 0.8976 0.02369 0.01505 -0.0299 0.2158 1.0000 8.000 0.8946 0.02570 0.01660 -0.0273 0.1502 1.0000 8.250 0.8964 0.02756 0.01810 -0.0253 0.1035 1.0000 9.000 0.9214 0.03212 0.02238 -0.0212 0.0602 1.0000 9.250 0.9304 0.03364 0.02392 -0.0200 0.0554 1.0000 9.500 0.9408 0.03509 0.02543 -0.0190 0.0516 1.0000 9.750 0.9501 0.03664 0.02700 -0.0180 0.0488 1.0000 10.000 0.9604 0.03816 0.02858 -0.0170 0.0460 1.0000 10.250 0.9722 0.03961 0.03011 -0.0161 0.0434 1.0000 10.500 0.9838 0.04112 0.03167 -0.0152 0.0415 1.0000 10.750 0.9959 0.04269 0.03322 -0.0144 0.0400 1.0000 11.000 1.0120 0.04411 0.03468 -0.0137 0.0387 1.0000 11.250 1.0298 0.04545 0.03616 -0.0131 0.0371 1.0000 11.500 1.0466 0.04688 0.03769 -0.0125 0.0354 1.0000 11.750 1.0628 0.04839 0.03927 -0.0121 0.0340 1.0000 12.000 1.0816 0.04994 0.04084 -0.0117 0.0330 1.0000 12.250 1.1050 0.05166 0.04259 -0.0115 0.0322 1.0000 12.500 1.1222 0.05365 0.04485 -0.0110 0.0315 1.0000 12.750 1.1367 0.05593 0.04741 -0.0104 0.0310 1.0000 13.000 1.1469 0.05848 0.05023 -0.0098 0.0304 1.0000 13.250 1.1521 0.06126 0.05328 -0.0092 0.0298 1.0000 13.500 1.1539 0.06420 0.05648 -0.0086 0.0293 1.0000 13.750 1.1533 0.06732 0.05983 -0.0082 0.0287 1.0000 14.000 1.1511 0.07053 0.06326 -0.0079 0.0282 1.0000 14.250 1.1472 0.07396 0.06689 -0.0079 0.0278 1.0000 14.500 1.1403 0.07779 0.07094 -0.0081 0.0275 1.0000 14.750 1.1311 0.08196 0.07534 -0.0086 0.0273 1.0000 15.000 1.1181 0.08678 0.08040 -0.0095 0.0272 1.0000 15.250 1.1026 0.09212 0.08600 -0.0110 0.0272 1.0000 15.500 1.0833 0.09829 0.09242 -0.0133 0.0272 1.0000 15.750 1.0596 0.10561 0.10002 -0.0166 0.0273 1.0000 16.000 1.0263 0.11537 0.11009 -0.0220 0.0275 1.0000 16.250 0.9691 0.13228 0.12737 -0.0330 0.0282 1.0000