XFOIL Version 6.96 Calculated polar for: EPPLER 342 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3522 0.10436 0.09971 -0.0251 1.0000 0.0481 -9.750 -0.3507 0.10070 0.09611 -0.0265 1.0000 0.0485 -9.500 -0.3506 0.09689 0.09236 -0.0281 1.0000 0.0490 -9.250 -0.2914 0.07894 0.07481 -0.0375 1.0000 0.0289 -9.000 -0.2862 0.07624 0.07217 -0.0368 1.0000 0.0280 -8.000 -0.4268 0.06683 0.06231 -0.0361 0.9859 0.0242 -7.750 -0.4064 0.06251 0.05781 -0.0401 0.9017 0.0235 -7.500 -0.3914 0.05788 0.05284 -0.0426 0.8544 0.0227 -7.000 -0.3916 0.04825 0.04217 -0.0379 0.7945 0.0205 -6.750 -0.3826 0.04591 0.03953 -0.0359 0.7700 0.0202 -6.500 -0.3740 0.04328 0.03656 -0.0334 0.7494 0.0201 -6.250 -0.3642 0.04060 0.03349 -0.0308 0.7317 0.0199 -5.750 -0.3378 0.03565 0.02769 -0.0259 0.7004 0.0197 -5.500 -0.3211 0.03322 0.02476 -0.0237 0.6866 0.0199 -5.250 -0.3017 0.03098 0.02198 -0.0218 0.6729 0.0208 -5.000 -0.2799 0.02975 0.02056 -0.0208 0.6593 0.0216 -4.750 -0.2567 0.02841 0.01887 -0.0197 0.6468 0.0230 -4.500 -0.2301 0.02664 0.01660 -0.0188 0.6354 0.0242 -4.250 -0.2024 0.02521 0.01495 -0.0184 0.6234 0.0249 -4.000 -0.1747 0.02406 0.01365 -0.0181 0.6125 0.0260 -3.750 -0.1466 0.02299 0.01240 -0.0178 0.6020 0.0274 -3.500 -0.1197 0.02206 0.01135 -0.0173 0.5914 0.0293 -3.250 -0.0948 0.02143 0.01057 -0.0166 0.5826 0.0338 -3.000 -0.0717 0.02073 0.00990 -0.0157 0.5728 0.0371 -2.750 -0.0493 0.02013 0.00919 -0.0144 0.5652 0.0426 -2.500 -0.0267 0.01962 0.00865 -0.0133 0.5562 0.0519 -2.250 -0.0037 0.01909 0.00810 -0.0121 0.5488 0.0703 -2.000 0.0882 0.01764 0.00974 -0.0212 0.5367 0.8403 -1.750 0.1304 0.01916 0.01091 -0.0214 0.5292 0.9018 -1.500 0.2237 0.02002 0.01135 -0.0322 0.5178 0.9458 -1.250 0.2634 0.01996 0.01102 -0.0346 0.5106 0.9561 -1.000 0.2938 0.01987 0.01076 -0.0354 0.5032 0.9609 -0.750 0.3223 0.01982 0.01049 -0.0357 0.4975 0.9655 -0.500 0.3547 0.01969 0.01023 -0.0369 0.4913 0.9691 -0.250 0.3838 0.01965 0.01005 -0.0375 0.4853 0.9731 0.000 0.4130 0.01960 0.00982 -0.0381 0.4803 0.9766 0.250 0.4441 0.01952 0.00966 -0.0391 0.4742 0.9797 0.500 0.4731 0.01950 0.00954 -0.0396 0.4686 0.9830 0.750 0.5017 0.01950 0.00941 -0.0401 0.4642 0.9860 1.000 0.5323 0.01947 0.00929 -0.0410 0.4596 0.9886 1.250 0.5614 0.01948 0.00927 -0.0417 0.4544 0.9913 1.500 0.5900 0.01951 0.00923 -0.0422 0.4496 0.9940 1.750 0.6196 0.01951 0.00910 -0.0429 0.4458 0.9962 2.000 0.6487 0.01956 0.00918 -0.0436 0.4410 0.9985 2.250 0.6757 0.01966 0.00927 -0.0438 0.4366 1.0000 2.500 0.6982 0.01982 0.00939 -0.0431 0.4328 1.0000 2.750 0.7208 0.01998 0.00948 -0.0423 0.4295 1.0000 3.000 0.7428 0.02021 0.00975 -0.0416 0.4253 1.0000 3.250 0.7647 0.02043 0.01001 -0.0408 0.4210 1.0000 3.500 0.7869 0.02065 0.01022 -0.0400 0.4175 1.0000 3.750 0.8093 0.02084 0.01039 -0.0392 0.4142 1.0000 4.000 0.8313 0.02109 0.01064 -0.0384 0.4108 1.0000 4.250 0.8522 0.02140 0.01105 -0.0375 0.4066 1.0000 4.500 0.8736 0.02168 0.01137 -0.0367 0.4028 1.0000 4.750 0.8954 0.02192 0.01164 -0.0358 0.3994 1.0000 5.000 0.9178 0.02214 0.01183 -0.0350 0.3965 1.0000 5.250 0.9377 0.02252 0.01233 -0.0340 0.3926 1.0000 5.500 0.9574 0.02290 0.01282 -0.0329 0.3886 1.0000 5.750 0.9780 0.02321 0.01320 -0.0319 0.3849 1.0000 6.000 0.9994 0.02346 0.01346 -0.0310 0.3817 1.0000 6.250 1.0204 0.02378 0.01379 -0.0300 0.3786 1.0000 6.500 1.0372 0.02429 0.01452 -0.0285 0.3742 1.0000 6.750 1.0556 0.02470 0.01504 -0.0272 0.3702 1.0000 7.000 1.0756 0.02501 0.01539 -0.0261 0.3667 1.0000 7.250 1.0972 0.02525 0.01564 -0.0252 0.3638 1.0000 7.500 1.1112 0.02588 0.01648 -0.0233 0.3593 1.0000 7.750 1.1266 0.02639 0.01713 -0.0216 0.3549 1.0000 8.000 1.1448 0.02672 0.01753 -0.0202 0.3511 1.0000 8.250 1.1659 0.02691 0.01773 -0.0192 0.3479 1.0000 8.500 1.1759 0.02766 0.01871 -0.0168 0.3432 1.0000 8.750 1.1881 0.02821 0.01942 -0.0146 0.3385 1.0000 9.000 1.2051 0.02849 0.01977 -0.0130 0.3345 1.0000 9.250 1.2234 0.02873 0.02004 -0.0116 0.3310 1.0000 9.500 1.2257 0.02964 0.02121 -0.0081 0.3256 1.0000 9.750 1.2360 0.03011 0.02180 -0.0056 0.3210 1.0000 10.000 1.2541 0.03019 0.02189 -0.0041 0.3170 1.0000 10.250 1.2531 0.03106 0.02298 -0.0002 0.3121 1.0000 10.500 1.2531 0.03178 0.02385 0.0037 0.3071 1.0000 10.750 1.2646 0.03193 0.02405 0.0062 0.3027 1.0000 11.000 1.2621 0.03262 0.02486 0.0104 0.2984 1.0000 11.250 1.2408 0.03366 0.02605 0.0172 0.2939 1.0000 11.500 1.2304 0.03422 0.02668 0.0225 0.2898 1.0000 11.750 1.2395 0.03423 0.02668 0.0253 0.2857 1.0000 12.000 1.1988 0.03650 0.02912 0.0322 0.2816 1.0000 12.250 1.1758 0.03863 0.03135 0.0361 0.2766 1.0000 12.500 1.1926 0.03850 0.03123 0.0375 0.2717 1.0000 12.750 1.1348 0.04446 0.03736 0.0399 0.2657 1.0000 13.000 1.1279 0.04680 0.03976 0.0407 0.2597 1.0000 13.250 1.0680 0.05536 0.04841 0.0396 0.2515 1.0000 13.500 1.0711 0.05714 0.05024 0.0399 0.2453 1.0000 13.750 1.0051 0.06796 0.06108 0.0372 0.2339 1.0000 14.000 1.0406 0.06561 0.05882 0.0386 0.2306 1.0000 14.250 0.9899 0.07511 0.06835 0.0360 0.2195 1.0000 14.500 1.0270 0.07240 0.06572 0.0375 0.2163 1.0000 14.750 0.9836 0.08138 0.07474 0.0347 0.2057 1.0000 15.000 1.0207 0.07858 0.07201 0.0362 0.2024 1.0000 15.250 0.9812 0.08741 0.08089 0.0332 0.1923 1.0000 15.500 1.0177 0.08459 0.07813 0.0347 0.1886 1.0000 15.750 0.9830 0.09300 0.08662 0.0318 0.1793 1.0000 16.000 1.0170 0.09048 0.08413 0.0331 0.1751 1.0000 16.250 0.9860 0.09858 0.09231 0.0301 0.1665 1.0000 16.500 1.0154 0.09677 0.09053 0.0311 0.1618 1.0000