XFOIL Version 6.96 Calculated polar for: NACA 0008 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.9223 0.05195 0.04936 -0.0182 1.0000 0.0104 -10.500 -0.9411 0.04749 0.04468 -0.0183 1.0000 0.0104 -10.250 -0.9556 0.04279 0.03965 -0.0172 1.0000 0.0103 -10.000 -0.9645 0.03782 0.03427 -0.0157 1.0000 0.0104 -9.750 -0.9671 0.03305 0.02904 -0.0140 1.0000 0.0105 -9.500 -0.9605 0.02943 0.02502 -0.0125 1.0000 0.0108 -9.250 -0.9448 0.02751 0.02289 -0.0115 1.0000 0.0112 -9.000 -0.9238 0.02675 0.02204 -0.0110 1.0000 0.0119 -8.750 -0.9034 0.02563 0.02077 -0.0103 1.0000 0.0126 -8.500 -0.8839 0.02395 0.01886 -0.0094 1.0000 0.0133 -8.250 -0.8640 0.02214 0.01678 -0.0083 1.0000 0.0139 -8.000 -0.8422 0.02077 0.01520 -0.0075 1.0000 0.0145 -7.750 -0.8201 0.01943 0.01363 -0.0066 1.0000 0.0151 -7.500 -0.8022 0.01694 0.01091 -0.0053 1.0000 0.0170 -7.250 -0.7771 0.01661 0.01055 -0.0049 1.0000 0.0188 -7.000 -0.7525 0.01604 0.00990 -0.0044 1.0000 0.0208 -6.750 -0.7273 0.01558 0.00935 -0.0038 1.0000 0.0226 -6.500 -0.7060 0.01420 0.00787 -0.0028 1.0000 0.0257 -6.250 -0.6807 0.01388 0.00752 -0.0024 1.0000 0.0292 -6.000 -0.6549 0.01364 0.00722 -0.0020 1.0000 0.0322 -5.750 -0.6328 0.01260 0.00612 -0.0011 1.0000 0.0361 -5.500 -0.6080 0.01224 0.00575 -0.0006 1.0000 0.0396 -5.250 -0.5831 0.01190 0.00536 0.0000 1.0000 0.0421 -5.000 -0.5583 0.01159 0.00498 0.0006 1.0000 0.0438 -4.750 -0.5354 0.01089 0.00423 0.0015 1.0000 0.0473 -4.500 -0.5111 0.01051 0.00384 0.0022 1.0000 0.0508 -4.250 -0.4865 0.01020 0.00350 0.0029 1.0000 0.0545 -4.000 -0.4623 0.00978 0.00309 0.0036 1.0000 0.0622 -3.750 -0.4382 0.00933 0.00274 0.0043 1.0000 0.0848 -3.500 -0.4153 0.00865 0.00243 0.0050 1.0000 0.1594 -3.250 -0.3916 0.00813 0.00222 0.0056 1.0000 0.2319 -3.000 -0.3676 0.00770 0.00205 0.0061 1.0000 0.3013 -2.750 -0.3432 0.00732 0.00192 0.0066 1.0000 0.3687 -2.500 -0.3186 0.00698 0.00183 0.0070 1.0000 0.4337 -2.250 -0.2937 0.00668 0.00176 0.0075 1.0000 0.4974 -2.000 -0.2688 0.00636 0.00173 0.0079 1.0000 0.5690 -1.750 -0.2437 0.00610 0.00172 0.0084 1.0000 0.6356 -1.500 -0.2147 0.00584 0.00173 0.0081 0.9986 0.7048 -1.250 -0.1771 0.00557 0.00175 0.0061 0.9942 0.7774 -1.000 -0.1420 0.00536 0.00179 0.0049 0.9882 0.8432 -0.750 -0.1059 0.00527 0.00183 0.0035 0.9823 0.8865 -0.500 -0.0686 0.00523 0.00185 0.0019 0.9757 0.9140 -0.250 -0.0346 0.00521 0.00185 0.0010 0.9651 0.9359 0.000 0.0000 0.00521 0.00186 0.0000 0.9521 0.9521 0.250 0.0346 0.00521 0.00185 -0.0010 0.9359 0.9651 0.500 0.0686 0.00523 0.00185 -0.0019 0.9139 0.9757 0.750 0.1059 0.00527 0.00183 -0.0035 0.8865 0.9823 1.000 0.1420 0.00536 0.00179 -0.0049 0.8433 0.9882 1.250 0.1771 0.00557 0.00175 -0.0061 0.7780 0.9942 1.500 0.2147 0.00584 0.00173 -0.0081 0.7047 0.9986 1.750 0.2437 0.00610 0.00172 -0.0084 0.6347 1.0000 2.000 0.2688 0.00636 0.00173 -0.0079 0.5686 1.0000 2.250 0.2937 0.00667 0.00176 -0.0075 0.4978 1.0000 2.500 0.3186 0.00698 0.00183 -0.0070 0.4337 1.0000 2.750 0.3432 0.00732 0.00192 -0.0066 0.3688 1.0000 3.000 0.3676 0.00770 0.00205 -0.0061 0.3011 1.0000 3.250 0.3917 0.00814 0.00222 -0.0056 0.2317 1.0000 3.500 0.4153 0.00865 0.00243 -0.0050 0.1594 1.0000 3.750 0.4382 0.00933 0.00274 -0.0043 0.0848 1.0000 4.000 0.4623 0.00978 0.00309 -0.0036 0.0622 1.0000 4.250 0.4865 0.01020 0.00350 -0.0029 0.0545 1.0000 4.500 0.5111 0.01050 0.00384 -0.0022 0.0509 1.0000 4.750 0.5354 0.01089 0.00423 -0.0015 0.0473 1.0000 5.000 0.5584 0.01159 0.00498 -0.0006 0.0438 1.0000 5.250 0.5832 0.01190 0.00536 0.0000 0.0421 1.0000 5.500 0.6081 0.01224 0.00575 0.0006 0.0396 1.0000 5.750 0.6329 0.01261 0.00613 0.0011 0.0361 1.0000 6.000 0.6550 0.01364 0.00722 0.0020 0.0322 1.0000 6.250 0.6807 0.01388 0.00753 0.0024 0.0292 1.0000 6.500 0.7060 0.01420 0.00787 0.0028 0.0257 1.0000 6.750 0.7273 0.01557 0.00934 0.0038 0.0226 1.0000 7.000 0.7525 0.01604 0.00990 0.0044 0.0209 1.0000 7.250 0.7771 0.01660 0.01055 0.0049 0.0188 1.0000 7.500 0.8022 0.01694 0.01091 0.0053 0.0170 1.0000 7.750 0.8201 0.01942 0.01362 0.0066 0.0151 1.0000 8.000 0.8422 0.02077 0.01520 0.0075 0.0145 1.0000 8.250 0.8640 0.02214 0.01679 0.0083 0.0139 1.0000 8.500 0.8838 0.02396 0.01887 0.0094 0.0133 1.0000 8.750 0.9034 0.02562 0.02076 0.0103 0.0126 1.0000 9.000 0.9238 0.02675 0.02204 0.0110 0.0119 1.0000 9.250 0.9448 0.02749 0.02287 0.0115 0.0112 1.0000 9.500 0.9604 0.02942 0.02502 0.0125 0.0108 1.0000 9.750 0.9670 0.03306 0.02905 0.0140 0.0105 1.0000 10.000 0.9646 0.03780 0.03425 0.0157 0.0104 1.0000 10.250 0.9555 0.04282 0.03968 0.0172 0.0103 1.0000 10.500 0.9412 0.04751 0.04469 0.0182 0.0104 1.0000 10.750 0.9221 0.05202 0.04944 0.0181 0.0104 1.0000 11.000 0.8994 0.05928 0.05694 0.0122 0.0106 1.0000