XFOIL Version 6.96 Calculated polar for: EPPLER 331 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4701 0.08432 0.08281 -0.0112 1.0000 0.0067 -8.750 -0.4767 0.07907 0.07759 -0.0160 1.0000 0.0067 -8.500 -0.4856 0.07472 0.07322 -0.0185 1.0000 0.0067 -8.250 -0.4982 0.07073 0.06920 -0.0187 1.0000 0.0067 -8.000 -0.5089 0.06752 0.06595 -0.0171 1.0000 0.0067 -7.750 -0.5134 0.06375 0.06212 -0.0162 1.0000 0.0067 -7.500 -0.4951 0.05759 0.05556 -0.0207 0.8692 0.0067 -7.250 -0.4965 0.05441 0.05206 -0.0182 0.8089 0.0067 -7.000 -0.5070 0.04986 0.04726 -0.0154 0.7775 0.0069 -6.750 -0.5014 0.04716 0.04435 -0.0135 0.7507 0.0070 -6.500 -0.4930 0.04455 0.04155 -0.0117 0.7287 0.0071 -6.000 -0.4709 0.03935 0.03594 -0.0079 0.6905 0.0073 -5.750 -0.4581 0.03660 0.03297 -0.0059 0.6749 0.0076 -5.500 -0.4442 0.03370 0.02983 -0.0036 0.6605 0.0079 -5.250 -0.4292 0.03050 0.02635 -0.0010 0.6471 0.0083 -5.000 -0.4112 0.02629 0.02154 0.0032 0.6354 0.0091 -4.750 -0.3996 0.02254 0.01748 0.0057 0.6233 0.0095 -4.500 -0.3785 0.02133 0.01612 0.0068 0.6096 0.0097 -4.250 -0.3565 0.02004 0.01462 0.0080 0.5967 0.0102 -4.000 -0.3319 0.01416 0.00778 0.0116 0.5876 0.0069 -3.750 -0.3063 0.01307 0.00654 0.0122 0.5756 0.0071 -3.500 -0.2807 0.01263 0.00606 0.0127 0.5632 0.0076 -3.000 -0.2299 0.01150 0.00474 0.0140 0.5408 0.0079 -2.750 -0.2049 0.01106 0.00421 0.0147 0.5304 0.0082 -2.250 -0.1534 0.01056 0.00358 0.0159 0.5093 0.0090 -2.000 -0.1293 0.01012 0.00307 0.0168 0.5001 0.0092 -1.750 -0.1048 0.00975 0.00264 0.0176 0.4908 0.0095 -1.500 -0.0794 0.00949 0.00233 0.0183 0.4821 0.0099 -1.000 -0.0296 0.00891 0.00180 0.0198 0.4650 0.0463 -0.750 -0.0062 0.00856 0.00169 0.0206 0.4569 0.1295 -0.500 0.0040 0.00721 0.00147 0.0237 0.4507 0.4757 -0.250 -0.0006 0.00574 0.00141 0.0307 0.4449 0.8573 0.000 0.0212 0.00602 0.00175 0.0328 0.4380 0.9140 0.250 0.0478 0.00640 0.00212 0.0338 0.4307 0.9308 0.500 0.0779 0.00673 0.00238 0.0338 0.4236 0.9386 0.750 0.1146 0.00712 0.00271 0.0325 0.4159 0.9455 1.000 0.1683 0.00757 0.00307 0.0273 0.4078 0.9480 1.250 0.2168 0.00782 0.00324 0.0230 0.3999 0.9492 1.500 0.2467 0.00788 0.00324 0.0226 0.3938 0.9505 1.750 0.2740 0.00790 0.00323 0.0227 0.3882 0.9522 2.000 0.2775 0.00789 0.00319 0.0279 0.3839 0.9577 2.250 0.3094 0.00792 0.00317 0.0270 0.3780 0.9581 2.500 0.3415 0.00794 0.00317 0.0260 0.3724 0.9585 2.750 0.3726 0.00800 0.00317 0.0252 0.3665 0.9589 3.000 0.4033 0.00803 0.00318 0.0245 0.3617 0.9594 3.250 0.4341 0.00806 0.00319 0.0237 0.3561 0.9599 3.500 0.4642 0.00814 0.00323 0.0231 0.3503 0.9605 3.750 0.4937 0.00817 0.00325 0.0227 0.3455 0.9611 4.000 0.5231 0.00822 0.00329 0.0222 0.3402 0.9618 4.250 0.5519 0.00832 0.00334 0.0219 0.3342 0.9626 4.500 0.5803 0.00834 0.00339 0.0216 0.3296 0.9634 4.750 0.6073 0.00840 0.00343 0.0216 0.3241 0.9644 5.000 0.6332 0.00848 0.00350 0.0219 0.3187 0.9654 5.250 0.6591 0.00852 0.00356 0.0222 0.3137 0.9668 5.500 0.6794 0.00859 0.00362 0.0236 0.3084 0.9688 5.750 0.6921 0.00865 0.00367 0.0268 0.3036 0.9714 6.000 0.7222 0.00869 0.00373 0.0261 0.2978 0.9718 6.250 0.7516 0.00881 0.00383 0.0255 0.2905 0.9722 6.500 0.7815 0.00887 0.00392 0.0248 0.2850 0.9726 6.750 0.8113 0.00900 0.00403 0.0241 0.2771 0.9731 7.000 0.8412 0.00910 0.00416 0.0234 0.2702 0.9736 7.250 0.8699 0.00925 0.00430 0.0229 0.2621 0.9742 7.500 0.8982 0.00937 0.00444 0.0225 0.2543 0.9749 7.750 0.9256 0.00955 0.00460 0.0223 0.2452 0.9756 8.000 0.9528 0.00971 0.00477 0.0221 0.2358 0.9764 8.250 0.9793 0.00990 0.00496 0.0220 0.2259 0.9774 8.500 1.0046 0.01014 0.00518 0.0221 0.2140 0.9785 8.750 1.0285 0.01040 0.00542 0.0225 0.2019 0.9798 9.000 1.0493 0.01069 0.00568 0.0235 0.1890 0.9816 9.250 1.0683 0.01102 0.00597 0.0249 0.1747 0.9836 9.500 1.0962 0.01145 0.00634 0.0242 0.1556 0.9842 9.750 1.1228 0.01196 0.00678 0.0236 0.1371 0.9849 10.000 1.1484 0.01252 0.00726 0.0232 0.1181 0.9857 10.250 1.1720 0.01326 0.00788 0.0230 0.0960 0.9867 10.500 1.1955 0.01393 0.00847 0.0228 0.0791 0.9879 10.750 1.2183 0.01458 0.00908 0.0228 0.0667 0.9893 11.000 1.2382 0.01539 0.00980 0.0231 0.0527 0.9911 11.250 1.2579 0.01606 0.01045 0.0237 0.0445 0.9930 11.500 1.2789 0.01681 0.01118 0.0237 0.0364 0.9944 11.750 1.3029 0.01755 0.01193 0.0231 0.0307 0.9955 12.000 1.3256 0.01837 0.01277 0.0226 0.0254 0.9970 12.250 1.3477 0.01925 0.01366 0.0221 0.0214 0.9986 12.500 1.3682 0.02018 0.01463 0.0217 0.0184 1.0000 12.750 1.3435 0.02053 0.01505 0.0306 0.0181 1.0000 13.000 1.3249 0.02120 0.01576 0.0374 0.0174 1.0000 13.250 1.3166 0.02247 0.01706 0.0411 0.0156 1.0000 13.500 1.3160 0.02396 0.01864 0.0428 0.0148 1.0000 13.750 1.3153 0.02586 0.02059 0.0438 0.0132 1.0000 14.000 1.3142 0.02810 0.02290 0.0442 0.0119 1.0000 14.250 1.3148 0.03040 0.02528 0.0441 0.0109 1.0000 14.500 1.3115 0.03324 0.02818 0.0439 0.0098 1.0000 14.750 1.3080 0.03622 0.03126 0.0434 0.0094 1.0000 15.000 1.3050 0.03920 0.03432 0.0429 0.0087 1.0000 15.250 1.2990 0.04256 0.03777 0.0422 0.0082 1.0000 15.500 1.2918 0.04612 0.04141 0.0414 0.0079 1.0000 15.750 1.2815 0.05009 0.04546 0.0404 0.0074 1.0000 16.000 1.2757 0.05354 0.04899 0.0395 0.0067 1.0000 16.250 1.2666 0.05748 0.05301 0.0384 0.0064 1.0000 16.500 1.2574 0.06157 0.05718 0.0371 0.0059 1.0000 16.750 1.2459 0.06612 0.06182 0.0356 0.0055 1.0000 17.000 1.2367 0.07041 0.06616 0.0341 0.0046 1.0000 17.250 1.2246 0.07520 0.07109 0.0325 0.0054 1.0000 17.500 1.2201 0.07897 0.07492 0.0312 0.0048 1.0000 17.750 1.2088 0.08377 0.07980 0.0294 0.0045 1.0000 18.000 1.2000 0.08830 0.08441 0.0277 0.0042 1.0000 18.250 1.1873 0.09349 0.08968 0.0257 0.0040 1.0000 18.500 1.1780 0.09820 0.09446 0.0239 0.0034 1.0000 18.750 1.1672 0.10326 0.09963 0.0218 0.0038 1.0000 19.000 1.1584 0.10807 0.10450 0.0199 0.0033 1.0000 19.250 1.1484 0.11313 0.10965 0.0177 0.0033 1.0000