XFOIL Version 6.96 Calculated polar for: NACA 66-210 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.4029 0.09135 0.08798 -0.0394 1.0000 0.0439 -10.000 -0.4064 0.08692 0.08357 -0.0409 1.0000 0.0450 -9.750 -0.4125 0.08212 0.07880 -0.0429 1.0000 0.0464 -9.500 -0.4205 0.07710 0.07382 -0.0453 1.0000 0.0472 -9.250 -0.4325 0.07160 0.06837 -0.0483 1.0000 0.0477 -9.000 -0.4493 0.06602 0.06282 -0.0515 1.0000 0.0475 -8.750 -0.4705 0.06212 0.05895 -0.0516 1.0000 0.0471 -8.500 -0.4992 0.06023 0.05711 -0.0477 1.0000 0.0465 -8.250 -0.5306 0.05947 0.05640 -0.0420 1.0000 0.0455 -8.000 -0.5613 0.05849 0.05544 -0.0364 1.0000 0.0447 -7.750 -0.5750 0.05483 0.05168 -0.0357 0.9977 0.0455 -7.500 -0.5738 0.04938 0.04592 -0.0384 0.9924 0.0484 -7.250 -0.5677 0.04729 0.04312 -0.0394 0.9853 0.0503 -7.000 -0.6123 0.05711 0.05242 -0.0341 0.9878 0.0503 -6.250 -0.5155 0.02748 0.02288 -0.0427 0.9716 0.0680 -6.000 -0.5413 0.03971 0.03456 -0.0387 0.9734 0.0700 -5.750 -0.5161 0.03682 0.03128 -0.0400 0.9706 0.0806 -5.500 -0.4996 0.03525 0.02935 -0.0390 0.9656 0.0929 -5.250 -0.4764 0.03291 0.02703 -0.0392 0.9623 0.1003 -5.000 -0.4426 0.02789 0.02091 -0.0374 0.9598 0.0661 -4.750 -0.4066 0.02453 0.01703 -0.0370 0.9584 0.0476 -4.500 -0.3729 0.02230 0.01447 -0.0378 0.9570 0.0459 -4.250 -0.3455 0.02091 0.01290 -0.0375 0.9542 0.0461 -4.000 -0.3225 0.02018 0.01202 -0.0366 0.9501 0.0486 -3.750 -0.2938 0.01944 0.01117 -0.0368 0.9475 0.0500 -3.500 -0.2659 0.01796 0.00973 -0.0370 0.9456 0.0524 -3.250 -0.2358 0.01714 0.00892 -0.0378 0.9437 0.0561 -3.000 -0.2022 0.01669 0.00843 -0.0393 0.9422 0.0633 -2.750 -0.1927 0.01622 0.00799 -0.0361 0.9360 0.0692 -2.500 -0.1669 0.01578 0.00755 -0.0361 0.9331 0.0854 -2.250 -0.1624 0.01296 0.00748 -0.0326 0.9302 0.7063 -2.000 -0.1398 0.01352 0.00822 -0.0297 0.9282 0.8161 -1.750 -0.1390 0.01399 0.00872 -0.0234 0.9218 0.8438 -1.500 -0.1300 0.01468 0.00946 -0.0175 0.9180 0.8788 -1.250 -0.1117 0.01526 0.01002 -0.0136 0.9156 0.9065 -1.000 -0.0775 0.01567 0.01035 -0.0137 0.9145 0.9236 -0.750 -0.0247 0.01613 0.01072 -0.0179 0.9147 0.9385 -0.500 -0.0082 0.01622 0.01077 -0.0162 0.9093 0.9464 -0.250 0.0317 0.01628 0.01077 -0.0192 0.9068 0.9493 0.000 0.0715 0.01630 0.01075 -0.0221 0.9046 0.9521 0.250 0.1107 0.01629 0.01072 -0.0249 0.9026 0.9546 0.500 0.1477 0.01627 0.01068 -0.0272 0.9008 0.9572 0.750 0.1832 0.01633 0.01075 -0.0294 0.8975 0.9591 1.000 0.2156 0.01641 0.01085 -0.0310 0.8929 0.9619 1.250 0.2565 0.01639 0.01087 -0.0342 0.8903 0.9635 1.500 0.2992 0.01629 0.01083 -0.0375 0.8881 0.9646 1.750 0.3438 0.01613 0.01074 -0.0410 0.8862 0.9653 2.000 0.3604 0.01628 0.01095 -0.0394 0.8777 0.9713 2.250 0.4199 0.01512 0.00989 -0.0439 0.8675 0.9688 2.500 0.4638 0.01382 0.00866 -0.0449 0.8504 0.9689 2.750 0.4978 0.01247 0.00730 -0.0437 0.8276 0.9704 3.000 0.5280 0.01146 0.00632 -0.0425 0.7911 0.9725 3.250 0.5565 0.01083 0.00565 -0.0414 0.7343 0.9755 3.500 0.5529 0.01223 0.00523 -0.0346 0.3590 0.9828 3.750 0.5627 0.01478 0.00626 -0.0330 0.0751 0.9882 4.000 0.5900 0.01551 0.00700 -0.0334 0.0619 0.9923 4.250 0.6164 0.01645 0.00796 -0.0338 0.0545 0.9963 4.500 0.6462 0.01723 0.00878 -0.0348 0.0493 1.0000 4.750 0.6562 0.01790 0.00945 -0.0318 0.0471 1.0000 5.000 0.6667 0.01891 0.01044 -0.0289 0.0452 1.0000 5.250 0.6869 0.02091 0.01242 -0.0276 0.0437 1.0000 5.500 0.7024 0.02163 0.01328 -0.0253 0.0428 1.0000 5.750 0.7159 0.02224 0.01404 -0.0227 0.0409 1.0000 6.000 0.7346 0.02362 0.01557 -0.0209 0.0404 1.0000 6.250 0.7541 0.02541 0.01756 -0.0191 0.0405 1.0000 6.500 0.7737 0.02777 0.02018 -0.0174 0.0414 1.0000 6.750 0.7982 0.03102 0.02356 -0.0167 0.0446 1.0000 7.000 0.8238 0.03878 0.03296 -0.0104 0.0919 1.0000 7.250 0.8406 0.04090 0.03515 -0.0093 0.0855 1.0000 7.500 0.8472 0.04331 0.03794 -0.0069 0.0759 1.0000 7.750 0.8634 0.04606 0.04070 -0.0062 0.0717 1.0000 8.000 0.8641 0.04951 0.04453 -0.0036 0.0660 1.0000 8.250 0.8715 0.05179 0.04708 -0.0015 0.0611 1.0000 8.500 0.8834 0.05479 0.05010 -0.0008 0.0586 1.0000 8.750 0.8890 0.06485 0.05996 -0.0020 0.0561 1.0000 9.000 0.8751 0.06358 0.05929 0.0032 0.0548 1.0000 9.250 0.8607 0.06551 0.06162 0.0069 0.0512 1.0000 9.500 0.8491 0.06861 0.06487 0.0092 0.0497 1.0000 9.750 0.8344 0.07168 0.06805 0.0114 0.0488 1.0000 10.000 0.8172 0.07528 0.07174 0.0125 0.0483 1.0000