XFOIL Version 6.96 Calculated polar for: EPPLER 334 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.3130 0.10078 0.09920 -0.0242 1.0000 0.0074 -9.250 -0.3106 0.09744 0.09589 -0.0254 1.0000 0.0074 -9.000 -0.3110 0.09353 0.09199 -0.0273 1.0000 0.0075 -8.750 -0.3031 0.09011 0.08859 -0.0295 0.9987 0.0074 -8.500 -0.2783 0.08376 0.08221 -0.0391 0.9481 0.0075 -8.250 -0.2124 0.07370 0.07183 -0.0624 0.8735 0.0075 -8.000 -0.2214 0.07073 0.06855 -0.0635 0.7970 0.0075 -7.750 -0.2309 0.06787 0.06555 -0.0635 0.7630 0.0075 -7.500 -0.2366 0.06478 0.06233 -0.0634 0.7373 0.0075 -7.250 -0.2353 0.06160 0.05904 -0.0637 0.7179 0.0075 -7.000 -0.2334 0.05785 0.05517 -0.0640 0.7015 0.0075 -6.750 -0.2279 0.05452 0.05171 -0.0638 0.6865 0.0075 -6.500 -0.2292 0.05040 0.04746 -0.0633 0.6731 0.0077 -6.250 -0.2202 0.04781 0.04475 -0.0627 0.6594 0.0078 -6.000 -0.2089 0.04503 0.04183 -0.0620 0.6464 0.0079 -5.750 -0.1960 0.04262 0.03929 -0.0613 0.6342 0.0080 -5.500 -0.1819 0.04018 0.03670 -0.0604 0.6223 0.0082 -5.250 -0.1668 0.03754 0.03389 -0.0593 0.6114 0.0084 -5.000 -0.1504 0.03489 0.03107 -0.0581 0.6014 0.0086 -4.750 -0.1333 0.03205 0.02801 -0.0565 0.5918 0.0091 -4.500 -0.1184 0.02558 0.02100 -0.0524 0.5851 0.0102 -4.250 -0.0993 0.02416 0.01943 -0.0515 0.5749 0.0104 -4.000 -0.0782 0.02306 0.01820 -0.0507 0.5647 0.0107 -3.750 -0.0579 0.01973 0.01431 -0.0479 0.5566 0.0130 -3.500 -0.0350 0.01865 0.01316 -0.0474 0.5468 0.0133 -3.250 -0.0108 0.01799 0.01240 -0.0469 0.5381 0.0141 -3.000 0.0133 0.01631 0.01034 -0.0455 0.5297 0.0165 -2.750 0.0386 0.01553 0.00949 -0.0451 0.5212 0.0171 -2.250 0.0919 0.01222 0.00559 -0.0429 0.5053 0.0134 -2.000 0.1179 0.01134 0.00462 -0.0421 0.4975 0.0116 -1.750 0.1430 0.01050 0.00364 -0.0411 0.4907 0.0103 -1.500 0.1689 0.01024 0.00330 -0.0406 0.4829 0.0101 -1.250 0.1945 0.00990 0.00292 -0.0400 0.4761 0.0101 -1.000 0.2199 0.00958 0.00255 -0.0394 0.4689 0.0101 -0.750 0.2453 0.00928 0.00220 -0.0387 0.4627 0.0105 -0.500 0.2719 0.00912 0.00200 -0.0384 0.4564 0.0111 -0.250 0.2981 0.00899 0.00182 -0.0379 0.4498 0.0142 0.000 0.3235 0.00867 0.00170 -0.0374 0.4443 0.0786 0.250 0.3426 0.00772 0.00164 -0.0361 0.4389 0.4014 0.500 0.3453 0.00639 0.00180 -0.0308 0.4344 0.8889 0.750 0.3654 0.00656 0.00202 -0.0285 0.4296 0.9222 1.000 0.3826 0.00676 0.00223 -0.0254 0.4248 0.9419 1.250 0.4036 0.00690 0.00231 -0.0236 0.4195 0.9512 1.500 0.4281 0.00702 0.00239 -0.0224 0.4151 0.9582 1.750 0.4560 0.00715 0.00249 -0.0221 0.4104 0.9664 2.000 0.4955 0.00734 0.00260 -0.0244 0.4047 0.9702 2.250 0.5228 0.00739 0.00261 -0.0244 0.4003 0.9717 2.500 0.5484 0.00741 0.00261 -0.0239 0.3963 0.9735 2.750 0.5695 0.00744 0.00260 -0.0226 0.3919 0.9757 3.000 0.5999 0.00753 0.00263 -0.0232 0.3871 0.9763 3.250 0.6308 0.00757 0.00266 -0.0240 0.3833 0.9769 3.500 0.6611 0.00762 0.00270 -0.0247 0.3792 0.9774 3.750 0.6907 0.00771 0.00274 -0.0252 0.3746 0.9781 4.000 0.7201 0.00781 0.00281 -0.0257 0.3703 0.9788 4.250 0.7502 0.00785 0.00286 -0.0264 0.3665 0.9794 4.500 0.7798 0.00793 0.00292 -0.0269 0.3623 0.9802 4.750 0.8092 0.00805 0.00300 -0.0274 0.3576 0.9812 5.000 0.8384 0.00813 0.00309 -0.0279 0.3535 0.9822 5.250 0.8665 0.00819 0.00317 -0.0282 0.3494 0.9834 5.500 0.8922 0.00829 0.00324 -0.0279 0.3449 0.9850 5.750 0.9199 0.00842 0.00335 -0.0281 0.3401 0.9860 6.000 0.9511 0.00848 0.00345 -0.0291 0.3362 0.9865 6.250 0.9819 0.00859 0.00356 -0.0300 0.3312 0.9870 6.500 1.0118 0.00876 0.00370 -0.0308 0.3257 0.9876 6.750 1.0427 0.00883 0.00382 -0.0316 0.3214 0.9882 7.000 1.0727 0.00896 0.00394 -0.0324 0.3159 0.9889 7.250 1.1021 0.00912 0.00410 -0.0331 0.3096 0.9898 7.500 1.1321 0.00923 0.00424 -0.0339 0.3035 0.9907 8.000 1.1901 0.00955 0.00458 -0.0351 0.2904 0.9930 8.250 1.2173 0.00977 0.00478 -0.0354 0.2827 0.9944 8.500 1.2470 0.00993 0.00496 -0.0362 0.2756 0.9953 8.750 1.2759 0.01018 0.00520 -0.0369 0.2668 0.9964 9.000 1.3046 0.01041 0.00544 -0.0376 0.2567 0.9977 9.250 1.3330 0.01069 0.00571 -0.0383 0.2460 0.9990 9.500 1.3592 0.01100 0.00601 -0.0385 0.2348 1.0000 9.750 1.3692 0.01131 0.00628 -0.0354 0.2238 1.0000 10.000 1.3773 0.01163 0.00657 -0.0319 0.2119 1.0000 10.250 1.3903 0.01196 0.00688 -0.0294 0.2005 1.0000 10.500 1.4064 0.01240 0.00728 -0.0277 0.1872 1.0000 10.750 1.4227 0.01290 0.00773 -0.0261 0.1731 1.0000 11.000 1.4381 0.01347 0.00825 -0.0244 0.1587 1.0000 11.250 1.4523 0.01408 0.00880 -0.0226 0.1443 1.0000 11.500 1.4649 0.01471 0.00938 -0.0205 0.1312 1.0000 11.750 1.4736 0.01535 0.00999 -0.0177 0.1197 1.0000 12.000 1.4789 0.01614 0.01072 -0.0145 0.1052 1.0000 12.250 1.4872 0.01685 0.01141 -0.0120 0.0974 1.0000 12.500 1.4867 0.01800 0.01247 -0.0085 0.0814 1.0000 12.750 1.4939 0.01886 0.01335 -0.0062 0.0764 1.0000 13.000 1.4979 0.01995 0.01446 -0.0039 0.0692 1.0000 13.250 1.4981 0.02139 0.01589 -0.0016 0.0615 1.0000 13.500 1.4963 0.02316 0.01765 0.0003 0.0541 1.0000 13.750 1.5039 0.02445 0.01903 0.0013 0.0531 1.0000 14.000 1.4978 0.02696 0.02152 0.0026 0.0447 1.0000 14.250 1.5003 0.02895 0.02357 0.0032 0.0422 1.0000 14.500 1.4966 0.03165 0.02631 0.0036 0.0381 1.0000 14.750 1.4950 0.03427 0.02899 0.0038 0.0350 1.0000 15.000 1.4899 0.03734 0.03212 0.0039 0.0324 1.0000 15.250 1.4853 0.04044 0.03528 0.0038 0.0296 1.0000 15.500 1.4788 0.04382 0.03873 0.0035 0.0278 1.0000 15.750 1.4715 0.04735 0.04233 0.0031 0.0260 1.0000 16.000 1.4630 0.05109 0.04613 0.0026 0.0237 1.0000 16.250 1.4539 0.05502 0.05013 0.0019 0.0223 1.0000 16.500 1.4438 0.05919 0.05437 0.0011 0.0199 1.0000 16.750 1.4382 0.06291 0.05817 0.0002 0.0196 1.0000 17.000 1.4268 0.06744 0.06276 -0.0009 0.0180 1.0000 17.250 1.4198 0.07149 0.06690 -0.0020 0.0173 1.0000 17.500 1.4120 0.07572 0.07121 -0.0033 0.0161 1.0000 17.750 1.4028 0.08023 0.07579 -0.0047 0.0151 1.0000 18.000 1.3938 0.08477 0.08039 -0.0062 0.0137 1.0000 18.250 1.3874 0.08906 0.08477 -0.0077 0.0133 1.0000