XFOIL Version 6.96 Calculated polar for: EPPLER 333 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -8.500 -0.3495 0.09092 0.08770 -0.0274 1.0000 0.0313 -8.250 -0.3554 0.08708 0.08391 -0.0319 1.0000 0.0315 -8.000 -0.3670 0.08376 0.08061 -0.0342 1.0000 0.0317 -7.750 -0.3743 0.08087 0.07771 -0.0345 1.0000 0.0318 -7.500 -0.3787 0.07799 0.07479 -0.0343 1.0000 0.0319 -7.250 -0.3799 0.07525 0.07202 -0.0334 1.0000 0.0320 -7.000 -0.3866 0.07017 0.06699 -0.0322 1.0000 0.0324 -6.750 -0.3862 0.06678 0.06372 -0.0303 1.0000 0.0330 -6.500 -0.3684 0.06315 0.06011 -0.0322 0.9900 0.0340 -6.250 -0.3389 0.05876 0.05564 -0.0371 0.9628 0.0357 -6.000 -0.3048 0.05401 0.05065 -0.0426 0.9300 0.0387 -5.750 -0.2648 0.05221 0.04804 -0.0464 0.8927 0.0419 -5.500 -0.2506 0.04527 0.04108 -0.0480 0.8608 0.0436 -5.250 -0.2344 0.04290 0.03858 -0.0473 0.8297 0.0458 -5.000 -0.2140 0.04367 0.03867 -0.0446 0.8024 0.0536 -4.750 -0.2044 0.03899 0.03375 -0.0432 0.7826 0.0552 -4.500 -0.1885 0.03641 0.03119 -0.0425 0.7625 0.0584 -4.250 -0.1678 0.03562 0.03001 -0.0406 0.7442 0.0657 -4.000 -0.1529 0.03263 0.02671 -0.0390 0.7284 0.0701 -3.750 -0.1330 0.03083 0.02479 -0.0379 0.7125 0.0744 -3.500 -0.1134 0.02930 0.02285 -0.0362 0.6983 0.0847 -3.250 -0.0915 0.02777 0.02119 -0.0351 0.6844 0.0916 -3.000 -0.0707 0.02612 0.01930 -0.0339 0.6718 0.1037 -2.750 -0.0318 0.02134 0.01341 -0.0302 0.6617 0.0381 -2.500 -0.0028 0.02006 0.01159 -0.0287 0.6494 0.0322 -2.250 0.0248 0.01835 0.00969 -0.0280 0.6378 0.0313 -2.000 0.0520 0.01723 0.00837 -0.0273 0.6274 0.0314 -1.750 0.0782 0.01624 0.00728 -0.0265 0.6161 0.0323 -1.500 0.1017 0.01535 0.00642 -0.0255 0.6055 0.0363 -1.250 0.1255 0.01483 0.00581 -0.0244 0.5961 0.0431 -1.000 0.1473 0.01411 0.00511 -0.0229 0.5864 0.0619 -0.750 0.3589 0.01239 0.00569 -0.0555 0.5653 1.0000 -0.500 0.3820 0.01240 0.00557 -0.0548 0.5561 1.0000 -0.250 0.4053 0.01245 0.00547 -0.0541 0.5480 1.0000 0.000 0.4286 0.01249 0.00537 -0.0534 0.5400 1.0000 0.250 0.4520 0.01255 0.00533 -0.0527 0.5321 1.0000 0.500 0.4756 0.01262 0.00527 -0.0520 0.5247 1.0000 0.750 0.4992 0.01271 0.00527 -0.0513 0.5177 1.0000 1.000 0.5228 0.01279 0.00526 -0.0506 0.5104 1.0000 1.250 0.5465 0.01290 0.00529 -0.0500 0.5041 1.0000 1.500 0.5702 0.01299 0.00533 -0.0493 0.4973 1.0000 1.750 0.5942 0.01315 0.00535 -0.0487 0.4918 1.0000 2.000 0.6176 0.01323 0.00546 -0.0480 0.4847 1.0000 2.250 0.6416 0.01337 0.00551 -0.0473 0.4791 1.0000 2.500 0.6653 0.01352 0.00565 -0.0467 0.4735 1.0000 2.750 0.6889 0.01365 0.00576 -0.0460 0.4672 1.0000 3.000 0.7130 0.01383 0.00583 -0.0454 0.4623 1.0000 3.250 0.7362 0.01397 0.00605 -0.0447 0.4563 1.0000 3.500 0.7598 0.01411 0.00616 -0.0440 0.4507 1.0000 3.750 0.7836 0.01432 0.00632 -0.0434 0.4459 1.0000 4.000 0.8065 0.01448 0.00654 -0.0426 0.4399 1.0000 4.250 0.8301 0.01465 0.00669 -0.0419 0.4348 1.0000 4.500 0.8531 0.01487 0.00693 -0.0412 0.4297 1.0000 4.750 0.8756 0.01506 0.00717 -0.0403 0.4240 1.0000 5.000 0.8991 0.01526 0.00733 -0.0396 0.4192 1.0000 5.250 0.9212 0.01551 0.00766 -0.0387 0.4137 1.0000 5.500 0.9433 0.01570 0.00790 -0.0378 0.4080 1.0000 5.750 0.9668 0.01594 0.00807 -0.0371 0.4033 1.0000 6.000 0.9874 0.01618 0.00847 -0.0359 0.3973 1.0000 6.250 1.0093 0.01637 0.00868 -0.0350 0.3916 1.0000 6.500 1.0316 0.01664 0.00894 -0.0341 0.3866 1.0000 6.750 1.0514 0.01686 0.00930 -0.0328 0.3801 1.0000 7.000 1.0735 0.01706 0.00948 -0.0318 0.3747 1.0000 7.250 1.0928 0.01733 0.00989 -0.0304 0.3685 1.0000 7.500 1.1131 0.01751 0.01011 -0.0292 0.3622 1.0000 7.750 1.1332 0.01778 0.01041 -0.0279 0.3563 1.0000 8.000 1.1513 0.01798 0.01074 -0.0263 0.3493 1.0000 8.250 1.1720 0.01821 0.01094 -0.0251 0.3434 1.0000 8.500 1.1878 0.01843 0.01135 -0.0231 0.3360 1.0000 8.750 1.2078 0.01863 0.01149 -0.0218 0.3295 1.0000 9.000 1.2214 0.01883 0.01192 -0.0195 0.3214 1.0000 9.250 1.2392 0.01904 0.01211 -0.0178 0.3145 1.0000 9.500 1.2522 0.01924 0.01249 -0.0153 0.3059 1.0000 9.750 1.2669 0.01947 0.01277 -0.0132 0.2980 1.0000 10.000 1.2803 0.01967 0.01306 -0.0108 0.2892 1.0000 10.250 1.2926 0.01996 0.01348 -0.0083 0.2800 1.0000 10.500 1.3054 0.02026 0.01381 -0.0060 0.2707 1.0000 10.750 1.3168 0.02058 0.01420 -0.0035 0.2602 1.0000 11.000 1.3274 0.02099 0.01472 -0.0010 0.2487 1.0000 11.250 1.3370 0.02149 0.01530 0.0015 0.2369 1.0000 11.500 1.3443 0.02208 0.01594 0.0042 0.2245 1.0000 11.750 1.3473 0.02277 0.01666 0.0076 0.2128 1.0000 12.000 1.3486 0.02364 0.01758 0.0108 0.2008 1.0000 12.250 1.3482 0.02477 0.01872 0.0137 0.1885 1.0000 12.500 1.3461 0.02620 0.02016 0.0161 0.1768 1.0000 12.750 1.3429 0.02795 0.02194 0.0180 0.1655 1.0000 13.000 1.3393 0.02999 0.02404 0.0194 0.1543 1.0000 13.250 1.3346 0.03238 0.02648 0.0203 0.1441 1.0000 13.500 1.3275 0.03519 0.02931 0.0208 0.1347 1.0000 13.750 1.3188 0.03833 0.03244 0.0210 0.1268 1.0000 14.000 1.3122 0.04149 0.03569 0.0208 0.1181 1.0000 14.250 1.3029 0.04500 0.03920 0.0206 0.1115 1.0000 14.500 1.2938 0.04863 0.04289 0.0200 0.1043 1.0000 14.750 1.2850 0.05227 0.04657 0.0195 0.0984 1.0000 15.000 1.2763 0.05603 0.05040 0.0188 0.0928 1.0000 15.250 1.2671 0.05994 0.05431 0.0180 0.0873 1.0000 15.500 1.2587 0.06401 0.05847 0.0168 0.0818 1.0000 15.750 1.2504 0.06796 0.06240 0.0158 0.0771 1.0000 16.000 1.2438 0.07208 0.06668 0.0144 0.0722 1.0000 16.250 1.2365 0.07606 0.07061 0.0133 0.0680 1.0000 16.500 1.2303 0.08026 0.07494 0.0119 0.0637 1.0000 16.750 1.2247 0.08438 0.07913 0.0104 0.0600 1.0000 17.000 1.2189 0.08834 0.08305 0.0092 0.0558 1.0000 17.250 1.2142 0.09254 0.08740 0.0076 0.0528 1.0000