XFOIL Version 6.96 Calculated polar for: USA 33 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.2014 0.13841 0.13669 -0.0325 1.0000 0.0310 -13.500 -0.2271 0.13155 0.12980 -0.0365 1.0000 0.0324 -11.500 -0.7408 0.03225 0.02921 -0.0786 0.9701 0.0350 -11.250 -0.7301 0.02809 0.02463 -0.0795 0.9550 0.0354 -11.000 -0.6936 0.02537 0.02157 -0.0838 0.9411 0.0359 -10.750 -0.6428 0.02371 0.01962 -0.0898 0.9176 0.0363 -10.500 -0.6183 0.02170 0.01720 -0.0907 0.8699 0.0368 -10.250 -0.6025 0.02101 0.01633 -0.0887 0.8419 0.0370 -10.000 -0.5845 0.02058 0.01579 -0.0868 0.8249 0.0372 -9.750 -0.5661 0.02013 0.01523 -0.0850 0.8116 0.0374 -9.500 -0.5459 0.01978 0.01481 -0.0835 0.8006 0.0377 -9.250 -0.5264 0.01930 0.01423 -0.0819 0.7906 0.0379 -9.000 -0.5063 0.01877 0.01361 -0.0803 0.7807 0.0382 -8.750 -0.4852 0.01842 0.01317 -0.0789 0.7709 0.0385 -8.500 -0.4642 0.01789 0.01255 -0.0775 0.7613 0.0389 -8.250 -0.4437 0.01737 0.01189 -0.0760 0.7506 0.0392 -8.000 -0.4214 0.01692 0.01135 -0.0747 0.7404 0.0396 -7.750 -0.3998 0.01648 0.01078 -0.0733 0.7287 0.0399 -7.500 -0.3770 0.01607 0.01026 -0.0721 0.7165 0.0402 -7.250 -0.3543 0.01578 0.00985 -0.0708 0.7033 0.0405 -6.750 -0.3098 0.01456 0.00842 -0.0684 0.6715 0.0414 -6.500 -0.2863 0.01433 0.00813 -0.0673 0.6543 0.0418 -6.250 -0.2626 0.01408 0.00780 -0.0662 0.6389 0.0422 -5.750 -0.2138 0.01361 0.00718 -0.0643 0.6129 0.0430 -5.500 -0.1894 0.01339 0.00687 -0.0634 0.6015 0.0435 -5.250 -0.1640 0.01313 0.00655 -0.0626 0.5924 0.0439 -5.000 -0.1392 0.01292 0.00626 -0.0617 0.5828 0.0443 -4.750 -0.1131 0.01272 0.00601 -0.0611 0.5764 0.0448 -4.500 -0.0874 0.01259 0.00581 -0.0603 0.5692 0.0451 -4.250 -0.0627 0.01209 0.00526 -0.0595 0.5620 0.0457 -4.000 -0.0367 0.01178 0.00498 -0.0589 0.5570 0.0464 -3.750 -0.0108 0.01159 0.00477 -0.0582 0.5516 0.0470 -3.500 0.0149 0.01144 0.00460 -0.0575 0.5464 0.0476 -3.250 0.0404 0.01130 0.00442 -0.0568 0.5411 0.0482 -3.000 0.0670 0.01112 0.00424 -0.0562 0.5382 0.0489 -2.750 0.0934 0.01096 0.00407 -0.0556 0.5346 0.0494 -2.500 0.1197 0.01085 0.00394 -0.0550 0.5307 0.0499 -2.250 0.1446 0.01060 0.00368 -0.0541 0.5267 0.0506 -2.000 0.1691 0.01041 0.00347 -0.0532 0.5218 0.0514 -1.750 0.1949 0.01026 0.00334 -0.0525 0.5184 0.0522 -1.500 0.2211 0.01013 0.00323 -0.0519 0.5151 0.0532 -1.250 0.2470 0.01003 0.00312 -0.0512 0.5113 0.0541 -1.000 0.2726 0.00995 0.00303 -0.0504 0.5072 0.0549 -0.750 0.2972 0.00988 0.00292 -0.0495 0.5022 0.0557 -0.500 0.3218 0.00972 0.00278 -0.0486 0.4981 0.0571 -0.250 0.3476 0.00960 0.00269 -0.0479 0.4938 0.0582 0.000 0.3729 0.00952 0.00261 -0.0471 0.4888 0.0596 0.250 0.3975 0.00950 0.00256 -0.0461 0.4824 0.0609 0.500 0.4222 0.00940 0.00247 -0.0452 0.4765 0.0634 0.750 0.4472 0.00932 0.00240 -0.0444 0.4689 0.0661 1.000 0.4706 0.00930 0.00236 -0.0432 0.4604 0.0705 1.250 0.4940 0.00912 0.00234 -0.0421 0.4550 0.1069 1.500 0.5186 0.00911 0.00238 -0.0412 0.4462 0.1297 1.750 0.5437 0.00916 0.00242 -0.0405 0.4359 0.1399 2.000 0.5676 0.00924 0.00247 -0.0395 0.4208 0.1477 2.250 0.5914 0.00937 0.00253 -0.0385 0.4015 0.1524 2.500 0.6136 0.00951 0.00260 -0.0372 0.3810 0.1577 2.750 0.6357 0.00968 0.00270 -0.0359 0.3629 0.1620 3.000 0.6581 0.00986 0.00281 -0.0347 0.3487 0.1655 3.250 0.6813 0.00997 0.00289 -0.0336 0.3386 0.1698 3.500 0.7037 0.01010 0.00300 -0.0324 0.3296 0.1747 3.750 0.7272 0.01020 0.00309 -0.0314 0.3223 0.1785 4.000 0.7494 0.01036 0.00321 -0.0302 0.3143 0.1815 4.250 0.7725 0.01042 0.00328 -0.0291 0.3088 0.1863 4.500 0.7950 0.01052 0.00338 -0.0279 0.3024 0.1918 4.750 0.8164 0.01069 0.00351 -0.0266 0.2950 0.1964 5.000 0.8393 0.01075 0.00359 -0.0255 0.2892 0.2018 5.250 0.8595 0.01090 0.00372 -0.0239 0.2801 0.2082 5.500 0.8814 0.01101 0.00383 -0.0227 0.2739 0.2138 5.750 0.9017 0.01112 0.00394 -0.0211 0.2662 0.2225 6.000 0.9209 0.01127 0.00408 -0.0194 0.2580 0.2323 6.250 0.9369 0.01135 0.00421 -0.0170 0.2486 0.2671 6.500 0.9130 0.01016 0.00433 -0.0064 0.2454 0.8202 6.750 1.0375 0.01109 0.00537 -0.0279 0.2003 0.9700 7.000 1.0628 0.01172 0.00586 -0.0278 0.1795 0.9806 7.250 1.0966 0.01233 0.00635 -0.0295 0.1629 0.9850 7.500 1.1249 0.01286 0.00679 -0.0301 0.1502 0.9897 7.750 1.1533 0.01340 0.00723 -0.0308 0.1368 0.9934 8.000 1.1820 0.01424 0.00786 -0.0321 0.1083 0.9969 8.250 1.1951 0.01572 0.00905 -0.0310 0.0638 1.0000 8.500 1.1971 0.01607 0.00941 -0.0265 0.0623 1.0000 8.750 1.2009 0.01649 0.00984 -0.0224 0.0609 1.0000 9.000 1.2055 0.01699 0.01035 -0.0186 0.0597 1.0000 9.250 1.2116 0.01753 0.01090 -0.0153 0.0587 1.0000 9.500 1.2182 0.01815 0.01153 -0.0122 0.0577 1.0000 9.750 1.2263 0.01878 0.01219 -0.0096 0.0570 1.0000 10.000 1.2360 0.01943 0.01287 -0.0073 0.0566 1.0000 10.250 1.2453 0.02017 0.01364 -0.0051 0.0561 1.0000 10.500 1.2550 0.02096 0.01446 -0.0032 0.0558 1.0000 10.750 1.2644 0.02185 0.01538 -0.0014 0.0554 1.0000 11.000 1.2734 0.02282 0.01638 0.0003 0.0550 1.0000 11.250 1.2818 0.02390 0.01750 0.0019 0.0545 1.0000 11.500 1.2904 0.02504 0.01868 0.0033 0.0543 1.0000 11.750 1.2980 0.02630 0.01997 0.0046 0.0539 1.0000 12.000 1.3054 0.02763 0.02135 0.0058 0.0536 1.0000 12.250 1.3118 0.02911 0.02286 0.0070 0.0533 1.0000 12.500 1.3170 0.03075 0.02455 0.0080 0.0529 1.0000 12.750 1.3213 0.03251 0.02637 0.0089 0.0526 1.0000 13.000 1.3243 0.03446 0.02837 0.0098 0.0523 1.0000 13.250 1.3274 0.03648 0.03044 0.0105 0.0522 1.0000 13.500 1.3262 0.03895 0.03298 0.0111 0.0518 1.0000 13.750 1.3260 0.04142 0.03551 0.0116 0.0516 1.0000 14.000 1.3248 0.04407 0.03824 0.0120 0.0513 1.0000 14.250 1.3271 0.04640 0.04063 0.0122 0.0513 1.0000 14.500 1.3293 0.04880 0.04309 0.0123 0.0512 1.0000 14.750 1.3304 0.05137 0.04572 0.0124 0.0511 1.0000 15.000 1.3309 0.05404 0.04845 0.0124 0.0510 1.0000 15.250 1.3315 0.05670 0.05117 0.0124 0.0509 1.0000 15.500 1.3308 0.05959 0.05413 0.0122 0.0508 1.0000 15.750 1.3300 0.06250 0.05711 0.0120 0.0507 1.0000 16.000 1.3291 0.06550 0.06017 0.0117 0.0506 1.0000 16.250 1.3269 0.06866 0.06339 0.0114 0.0506 1.0000 16.500 1.3253 0.07180 0.06659 0.0110 0.0504 1.0000 16.750 1.3240 0.07497 0.06982 0.0104 0.0503 1.0000 17.000 1.3223 0.07817 0.07308 0.0099 0.0502 1.0000 17.250 1.3195 0.08158 0.07656 0.0093 0.0502 1.0000 17.500 1.3183 0.08479 0.07982 0.0087 0.0500 1.0000 17.750 1.3169 0.08810 0.08320 0.0079 0.0499 1.0000