XFOIL Version 6.96 Calculated polar for: EPPLER 340 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5344 0.09445 0.08812 -0.0127 1.0000 0.0436 -9.500 -0.5349 0.09045 0.08415 -0.0136 1.0000 0.0432 -9.250 -0.5411 0.08621 0.07991 -0.0146 1.0000 0.0429 -9.000 -0.5480 0.08227 0.07597 -0.0149 1.0000 0.0424 -8.750 -0.5568 0.07851 0.07218 -0.0145 1.0000 0.0419 -8.500 -0.5669 0.07496 0.06857 -0.0132 1.0000 0.0416 -8.250 -0.5739 0.07145 0.06497 -0.0118 1.0000 0.0411 -8.000 -0.5792 0.06792 0.06131 -0.0101 1.0000 0.0408 -7.750 -0.5820 0.06446 0.05769 -0.0081 1.0000 0.0404 -7.500 -0.5828 0.06108 0.05411 -0.0059 1.0000 0.0400 -7.250 -0.5813 0.05779 0.05060 -0.0036 1.0000 0.0396 -7.000 -0.5780 0.05457 0.04712 -0.0010 1.0000 0.0391 -6.750 -0.5731 0.05151 0.04377 0.0016 1.0000 0.0387 -6.500 -0.5669 0.04864 0.04063 0.0044 1.0000 0.0383 -6.250 -0.5575 0.04600 0.03770 0.0067 0.9927 0.0381 -6.000 -0.5251 0.04248 0.03367 0.0051 0.9375 0.0383 -5.750 -0.4888 0.03934 0.03000 0.0034 0.8988 0.0388 -5.500 -0.4542 0.03684 0.02699 0.0026 0.8655 0.0406 -5.250 -0.4220 0.03475 0.02427 0.0028 0.8362 0.0432 -5.000 -0.3918 0.03301 0.02231 0.0029 0.8100 0.0459 -4.750 -0.3574 0.03135 0.02036 0.0026 0.7857 0.0486 -4.500 -0.3176 0.02981 0.01852 0.0017 0.7637 0.0536 -4.250 -0.2779 0.02868 0.01707 0.0007 0.7437 0.0617 -4.000 -0.2457 0.02764 0.01588 0.0006 0.7255 0.0726 -3.500 -0.1968 0.02548 0.01383 0.0024 0.6935 0.1247 -3.250 -0.1355 0.02548 0.01704 0.0039 0.6775 0.8623 -3.000 0.0097 0.02692 0.01734 -0.0129 0.6525 0.9882 -2.750 0.0545 0.02621 0.01619 -0.0168 0.6379 0.9983 -2.500 0.0806 0.02594 0.01561 -0.0171 0.6257 1.0000 -2.250 0.1040 0.02579 0.01520 -0.0169 0.6136 1.0000 -2.000 0.1272 0.02566 0.01482 -0.0166 0.6033 1.0000 -1.750 0.1505 0.02557 0.01450 -0.0163 0.5931 1.0000 -1.500 0.1745 0.02551 0.01425 -0.0162 0.5832 1.0000 -1.250 0.1977 0.02547 0.01398 -0.0158 0.5747 1.0000 -1.000 0.2221 0.02548 0.01386 -0.0157 0.5652 1.0000 -0.750 0.2455 0.02548 0.01367 -0.0153 0.5576 1.0000 -0.500 0.2699 0.02556 0.01365 -0.0152 0.5488 1.0000 -0.250 0.2933 0.02562 0.01355 -0.0148 0.5416 1.0000 0.000 0.3175 0.02576 0.01359 -0.0147 0.5338 1.0000 0.250 0.3413 0.02589 0.01362 -0.0144 0.5267 1.0000 0.500 0.3649 0.02604 0.01366 -0.0140 0.5204 1.0000 0.750 0.3895 0.02627 0.01386 -0.0140 0.5129 1.0000 1.000 0.4130 0.02643 0.01390 -0.0135 0.5073 1.0000 1.250 0.4374 0.02674 0.01420 -0.0135 0.5005 1.0000 1.500 0.4612 0.02701 0.01445 -0.0133 0.4942 1.0000 1.750 0.4845 0.02720 0.01452 -0.0127 0.4895 1.0000 2.000 0.5087 0.02767 0.01507 -0.0129 0.4824 1.0000 2.250 0.5321 0.02799 0.01537 -0.0125 0.4767 1.0000 2.500 0.5553 0.02822 0.01552 -0.0118 0.4725 1.0000 2.750 0.5786 0.02886 0.01629 -0.0120 0.4655 1.0000 3.000 0.6016 0.02926 0.01670 -0.0116 0.4602 1.0000 3.250 0.6245 0.02953 0.01690 -0.0109 0.4563 1.0000 3.500 0.6466 0.03034 0.01787 -0.0110 0.4498 1.0000 3.750 0.6686 0.03087 0.01848 -0.0106 0.4445 1.0000 4.000 0.6911 0.03119 0.01877 -0.0098 0.4404 1.0000 4.250 0.7114 0.03209 0.01983 -0.0096 0.4342 1.0000 4.500 0.7319 0.03282 0.02069 -0.0091 0.4288 1.0000 4.750 0.7535 0.03321 0.02109 -0.0083 0.4247 1.0000 5.000 0.7723 0.03416 0.02217 -0.0077 0.4194 1.0000 5.250 0.7896 0.03523 0.02341 -0.0071 0.4134 1.0000 5.500 0.8099 0.03576 0.02400 -0.0062 0.4092 1.0000 5.750 0.8287 0.03649 0.02481 -0.0052 0.4048 1.0000 6.000 0.8404 0.03813 0.02669 -0.0044 0.3978 1.0000 6.250 0.8588 0.03875 0.02739 -0.0033 0.3934 1.0000 6.500 0.8802 0.03904 0.02772 -0.0021 0.3899 1.0000 6.750 0.8808 0.04168 0.03067 -0.0009 0.3819 1.0000 7.000 0.8971 0.04241 0.03149 0.0005 0.3773 1.0000 7.250 0.9201 0.04244 0.03155 0.0018 0.3741 1.0000 7.500 0.9041 0.04628 0.03571 0.0040 0.3652 1.0000 7.750 0.9203 0.04681 0.03632 0.0056 0.3608 1.0000 8.000 0.9269 0.04825 0.03787 0.0075 0.3559 1.0000 8.250 0.8979 0.05257 0.04235 0.0106 0.3475 1.0000 8.500 0.9213 0.05229 0.04215 0.0122 0.3438 1.0000 9.000 0.8435 0.06149 0.05141 0.0193 0.3287 1.0000 9.250 0.8722 0.06061 0.05062 0.0211 0.3258 1.0000 10.250 0.7571 0.07900 0.06896 0.0267 0.2937 1.0000 10.500 0.7284 0.08424 0.07419 0.0269 0.2845 1.0000 10.750 0.7483 0.08405 0.07410 0.0288 0.2810 1.0000 11.000 0.7160 0.08999 0.08001 0.0283 0.2711 1.0000 11.250 0.7312 0.09035 0.08048 0.0299 0.2669 1.0000 11.500 0.7095 0.09535 0.08547 0.0295 0.2585 1.0000 11.750 0.7184 0.09652 0.08674 0.0306 0.2532 1.0000 12.000 0.7114 0.09986 0.09011 0.0307 0.2466 1.0000 12.250 0.7087 0.10270 0.09301 0.0309 0.2400 1.0000 12.500 0.7305 0.10216 0.09260 0.0327 0.2364 1.0000 12.750 0.7036 0.10851 0.09893 0.0310 0.2269 1.0000 13.000 0.7210 0.10866 0.09921 0.0324 0.2227 1.0000