XFOIL Version 6.96 Calculated polar for: NACA 65(4)-421 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.6200 0.11792 0.11347 -0.0704 1.0000 0.0299 -18.250 -0.6900 0.10066 0.09582 -0.0805 1.0000 0.0297 -18.000 -0.7221 0.09190 0.08681 -0.0852 1.0000 0.0297 -17.750 -0.7453 0.08518 0.07987 -0.0885 1.0000 0.0298 -17.500 -0.7629 0.07963 0.07412 -0.0909 1.0000 0.0299 -17.250 -0.7778 0.07481 0.06910 -0.0927 1.0000 0.0301 -17.000 -0.7900 0.07053 0.06462 -0.0940 1.0000 0.0302 -16.750 -0.7992 0.06682 0.06073 -0.0949 1.0000 0.0304 -16.500 -0.8070 0.06345 0.05717 -0.0954 1.0000 0.0306 -16.250 -0.8133 0.06042 0.05396 -0.0957 1.0000 0.0309 -16.000 -0.8199 0.05756 0.05088 -0.0957 1.0000 0.0311 -15.750 -0.8190 0.05541 0.04862 -0.0955 1.0000 0.0314 -15.500 -0.8105 0.05388 0.04708 -0.0950 1.0000 0.0317 -15.250 -0.7881 0.05175 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-0.0653 0.6565 0.6373 -0.750 0.2120 0.01528 0.00739 -0.0656 0.6543 0.6399 -0.500 0.2404 0.01527 0.00733 -0.0661 0.6523 0.6428 -0.250 0.2694 0.01526 0.00725 -0.0667 0.6505 0.6456 0.000 0.2987 0.01526 0.00719 -0.0673 0.6488 0.6479 0.250 0.3238 0.01534 0.00733 -0.0671 0.6461 0.6496 0.500 0.3496 0.01541 0.00745 -0.0671 0.6432 0.6515 0.750 0.3761 0.01548 0.00755 -0.0671 0.6406 0.6538 1.000 0.4034 0.01554 0.00763 -0.0673 0.6383 0.6564 1.250 0.4313 0.01560 0.00768 -0.0677 0.6363 0.6591 1.500 0.4599 0.01564 0.00771 -0.0681 0.6344 0.6618 1.750 0.4893 0.01568 0.00771 -0.0688 0.6327 0.6646 2.000 0.5184 0.01574 0.00776 -0.0694 0.6308 0.6669 2.250 0.5412 0.01589 0.00802 -0.0688 0.6278 0.6689 2.500 0.5657 0.01604 0.00825 -0.0686 0.6252 0.6711 2.750 0.5912 0.01618 0.00845 -0.0685 0.6228 0.6738 3.000 0.6177 0.01629 0.00861 -0.0686 0.6204 0.6767 3.250 0.6455 0.01638 0.00872 -0.0689 0.6182 0.6798 3.500 0.6745 0.01644 0.00879 -0.0694 0.6162 0.6828 3.750 0.7043 0.01653 0.00887 -0.0702 0.6145 0.6857 4.000 0.7298 0.01668 0.00912 -0.0701 0.6123 0.6879 4.250 0.7493 0.01694 0.00951 -0.0690 0.6089 0.6904 4.500 0.7717 0.01714 0.00980 -0.0684 0.6058 0.6932 4.750 0.7968 0.01728 0.01001 -0.0682 0.6028 0.6964 5.000 0.8247 0.01734 0.01011 -0.0685 0.6000 0.7000 5.250 0.8554 0.01736 0.01014 -0.0693 0.5975 0.7037 5.500 0.8800 0.01749 0.01037 -0.0690 0.5944 0.7067 5.750 0.8940 0.01778 0.01081 -0.0670 0.5894 0.7095 6.000 0.9165 0.01785 0.01097 -0.0663 0.5848 0.7127 6.250 0.9474 0.01769 0.01083 -0.0669 0.5803 0.7161 6.500 0.9617 0.01784 0.01109 -0.0648 0.5736 0.7201 6.750 0.9803 0.01784 0.01113 -0.0634 0.5661 0.7244 7.000 1.0016 0.01775 0.01111 -0.0623 0.5591 0.7276 7.250 1.0043 0.01795 0.01144 -0.0581 0.5506 0.7318 7.500 1.0180 0.01797 0.01151 -0.0557 0.5410 0.7363 7.750 1.0291 0.01807 0.01162 -0.0531 0.5284 0.7412 8.000 1.0295 0.01860 0.01223 -0.0491 0.5144 0.7456 8.250 1.0328 0.01912 0.01281 -0.0457 0.4979 0.7499 8.500 1.0388 0.01968 0.01338 -0.0429 0.4795 0.7548 8.750 1.0412 0.02048 0.01413 -0.0398 0.4517 0.7604 9.000 1.0401 0.02146 0.01495 -0.0363 0.4149 0.7656 9.250 1.0307 0.02299 0.01627 -0.0321 0.3756 0.7711 9.500 1.0192 0.02489 0.01798 -0.0282 0.3401 0.7773 9.750 1.0084 0.02697 0.01989 -0.0248 0.3071 0.7834 10.000 0.9994 0.02904 0.02185 -0.0218 0.2784 0.7889 10.250 0.9907 0.03128 0.02397 -0.0191 0.2483 0.7951 10.500 0.9860 0.03345 0.02602 -0.0170 0.2209 0.8016 10.750 0.9818 0.03560 0.02809 -0.0150 0.1961 0.8074 11.000 0.9791 0.03779 0.03018 -0.0133 0.1702 0.8145 11.250 0.9781 0.03995 0.03224 -0.0119 0.1461 0.8216 11.500 0.9766 0.04215 0.03435 -0.0105 0.1218 0.8291 12.000 0.9779 0.04649 0.03849 -0.0083 0.0794 0.8452 12.250 0.9805 0.04860 0.04053 -0.0074 0.0636 0.8541 12.750 0.9887 0.05255 0.04447 -0.0058 0.0465 0.8738 13.000 0.9943 0.05439 0.04637 -0.0051 0.0425 0.8863 13.250 0.9993 0.05632 0.04835 -0.0044 0.0399 0.9020 13.500 1.0063 0.05815 0.05029 -0.0040 0.0377 0.9240 13.750 1.0129 0.06002 0.05227 -0.0042 0.0360 0.9820 14.250 1.0266 0.06447 0.05681 -0.0045 0.0331 1.0000 14.500 1.0335 0.06679 0.05918 -0.0048 0.0317 1.0000 14.750 1.0393 0.06925 0.06168 -0.0051 0.0310 1.0000 15.000 1.0437 0.07188 0.06434 -0.0055 0.0301 1.0000 15.250 1.0505 0.07428 0.06682 -0.0058 0.0293 1.0000 15.500 1.0568 0.07676 0.06938 -0.0063 0.0286 1.0000 15.750 1.0628 0.07928 0.07195 -0.0067 0.0280 1.0000 16.000 1.0683 0.08189 0.07462 -0.0073 0.0274 1.0000 16.250 1.0738 0.08451 0.07728 -0.0078 0.0269 1.0000 16.500 1.0789 0.08716 0.07997 -0.0084 0.0265 1.0000 16.750 1.0839 0.08981 0.08263 -0.0090 0.0260 1.0000 17.000 1.0915 0.09222 0.08513 -0.0096 0.0256 1.0000