XFOIL Version 6.96 Calculated polar for: NACA 64-209 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.6965 0.03106 0.02823 -0.0397 1.0000 0.0084 -8.000 -0.7009 0.02254 0.01895 -0.0372 1.0000 0.0084 -7.750 -0.6917 0.01770 0.01350 -0.0352 1.0000 0.0086 -7.500 -0.6755 0.01545 0.01093 -0.0337 1.0000 0.0088 -7.250 -0.6519 0.01391 0.00916 -0.0334 0.9990 0.0091 -7.000 -0.6194 0.01272 0.00781 -0.0349 0.9959 0.0094 -6.750 -0.5870 0.01184 0.00680 -0.0364 0.9924 0.0101 -6.500 -0.5547 0.01104 0.00589 -0.0377 0.9883 0.0107 -6.250 -0.5208 0.01035 0.00507 -0.0394 0.9847 0.0111 -6.000 -0.4881 0.00980 0.00442 -0.0407 0.9791 0.0116 -5.750 -0.4553 0.00938 0.00394 -0.0419 0.9722 0.0121 -5.500 -0.4237 0.00911 0.00366 -0.0428 0.9637 0.0131 -5.250 -0.3932 0.00905 0.00365 -0.0434 0.9541 0.0146 -5.000 -0.3640 0.00945 0.00418 -0.0435 0.9428 0.0158 -4.750 -0.3367 0.00949 0.00412 -0.0432 0.9309 0.0212 -4.500 -0.3092 0.00969 0.00430 -0.0430 0.9196 0.0227 -4.250 -0.2829 0.00955 0.00416 -0.0428 0.9085 0.0252 -4.000 -0.2562 0.00953 0.00410 -0.0426 0.8978 0.0272 -3.750 -0.2290 0.00950 0.00402 -0.0425 0.8870 0.0287 -3.500 -0.2012 0.00969 0.00418 -0.0425 0.8768 0.0298 -3.250 -0.1757 0.00909 0.00349 -0.0422 0.8666 0.0315 -3.000 -0.1495 0.00868 0.00304 -0.0421 0.8564 0.0328 -2.750 -0.1225 0.00840 0.00274 -0.0420 0.8465 0.0340 -2.500 -0.0954 0.00818 0.00250 -0.0420 0.8371 0.0360 -2.250 -0.0682 0.00800 0.00227 -0.0419 0.8274 0.0374 -2.000 -0.0406 0.00782 0.00206 -0.0419 0.8174 0.0382 -1.750 -0.0129 0.00767 0.00186 -0.0419 0.8078 0.0376 -1.250 0.0427 0.00743 0.00152 -0.0419 0.7886 0.0364 -1.000 0.0707 0.00735 0.00140 -0.0419 0.7794 0.0358 -0.500 0.1266 0.00721 0.00121 -0.0420 0.7599 0.0349 -0.250 0.1546 0.00715 0.00114 -0.0420 0.7503 0.0346 0.000 0.1825 0.00712 0.00107 -0.0420 0.7412 0.0343 0.250 0.2106 0.00707 0.00102 -0.0421 0.7312 0.0342 0.500 0.2386 0.00704 0.00098 -0.0421 0.7207 0.0342 0.750 0.2666 0.00703 0.00095 -0.0422 0.7095 0.0345 1.000 0.2944 0.00703 0.00092 -0.0422 0.6972 0.0353 1.250 0.3221 0.00704 0.00090 -0.0421 0.6792 0.0376 1.500 0.3474 0.00558 0.00081 -0.0427 0.6469 0.5823 1.750 0.3736 0.00538 0.00091 -0.0425 0.6189 0.6985 2.000 0.4005 0.00537 0.00100 -0.0424 0.5988 0.7452 2.250 0.4275 0.00542 0.00109 -0.0422 0.5749 0.7756 2.500 0.4540 0.00555 0.00120 -0.0419 0.5399 0.7983 2.750 0.4792 0.00580 0.00133 -0.0414 0.4814 0.8258 3.000 0.5012 0.00647 0.00159 -0.0405 0.3524 0.8533 3.250 0.5209 0.00753 0.00204 -0.0395 0.1839 0.8775 3.500 0.5429 0.00831 0.00240 -0.0387 0.0760 0.8931 3.750 0.5671 0.00871 0.00269 -0.0381 0.0404 0.9065 4.000 0.5915 0.00900 0.00299 -0.0373 0.0306 0.9207 4.250 0.6156 0.00916 0.00321 -0.0365 0.0270 0.9365 4.500 0.6375 0.00961 0.00373 -0.0352 0.0215 0.9573 4.750 0.6684 0.00976 0.00391 -0.0360 0.0201 0.9857 5.000 0.6969 0.01006 0.00423 -0.0363 0.0183 1.0000 5.250 0.7235 0.01045 0.00463 -0.0363 0.0169 1.0000 5.500 0.7477 0.01122 0.00547 -0.0358 0.0153 1.0000 5.750 0.7712 0.01208 0.00643 -0.0352 0.0147 1.0000 6.000 0.7970 0.01254 0.00693 -0.0350 0.0143 1.0000 6.250 0.8229 0.01295 0.00737 -0.0348 0.0136 1.0000 6.500 0.8481 0.01346 0.00792 -0.0345 0.0128 1.0000 6.750 0.8728 0.01405 0.00855 -0.0341 0.0121 1.0000 7.000 0.8971 0.01471 0.00927 -0.0337 0.0116 1.0000 7.250 0.9210 0.01544 0.01004 -0.0333 0.0112 1.0000 7.500 0.9431 0.01660 0.01128 -0.0326 0.0107 1.0000 7.750 0.9601 0.01984 0.01481 -0.0312 0.0101 1.0000 8.000 0.9852 0.02002 0.01505 -0.0309 0.0098 1.0000 8.250 1.0095 0.02050 0.01562 -0.0305 0.0093 1.0000 8.500 1.0314 0.02174 0.01702 -0.0298 0.0089 1.0000 8.750 1.0522 0.02313 0.01858 -0.0291 0.0085 1.0000 9.000 1.0720 0.02456 0.02017 -0.0282 0.0081 1.0000 9.250 1.0912 0.02587 0.02164 -0.0274 0.0078 1.0000 9.500 1.1095 0.02715 0.02306 -0.0265 0.0076 1.0000 9.750 1.1274 0.02825 0.02428 -0.0256 0.0074 1.0000 10.000 1.1414 0.02993 0.02613 -0.0244 0.0071 1.0000 10.250 1.1407 0.03397 0.03054 -0.0218 0.0069 1.0000 10.500 1.1117 0.04119 0.03837 -0.0172 0.0068 1.0000 10.750 1.0757 0.04646 0.04400 -0.0119 0.0067 1.0000 11.000 1.0619 0.04940 0.04710 -0.0097 0.0068 1.0000 11.250 1.0331 0.05454 0.05246 -0.0089 0.0067 1.0000 11.500 1.0082 0.06017 0.05827 -0.0102 0.0067 1.0000 11.750 0.9857 0.06658 0.06483 -0.0134 0.0068 1.0000 12.000 0.9701 0.07299 0.07136 -0.0175 0.0068 1.0000