XFOIL Version 6.96 Calculated polar for: EPPLER 341 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5466 0.07160 0.06850 -0.0172 0.6715 0.0078 -8.750 -0.5627 0.06675 0.06351 -0.0170 0.6608 0.0077 -8.500 -0.5758 0.06218 0.05876 -0.0155 0.6502 0.0076 -8.250 -0.5828 0.05735 0.05373 -0.0139 0.6401 0.0075 -7.250 -0.6086 0.02772 0.02189 0.0022 0.6118 0.0066 -7.000 -0.5924 0.02535 0.01914 0.0041 0.6005 0.0065 -6.750 -0.5730 0.02338 0.01681 0.0055 0.5892 0.0065 -6.500 -0.5513 0.02180 0.01491 0.0067 0.5779 0.0065 -6.250 -0.5279 0.02050 0.01334 0.0075 0.5663 0.0065 -6.000 -0.5035 0.01936 0.01198 0.0082 0.5557 0.0065 -5.750 -0.4784 0.01842 0.01084 0.0088 0.5462 0.0066 -5.500 -0.4530 0.01758 0.00984 0.0094 0.5364 0.0066 -5.250 -0.4276 0.01676 0.00888 0.0099 0.5277 0.0066 -5.000 -0.4027 0.01599 0.00799 0.0105 0.5183 0.0067 -4.750 -0.3780 0.01532 0.00724 0.0111 0.5094 0.0069 -4.500 -0.3531 0.01482 0.00665 0.0117 0.5003 0.0070 -4.250 -0.3279 0.01438 0.00615 0.0123 0.4922 0.0072 -4.000 -0.3028 0.01400 0.00570 0.0129 0.4844 0.0075 -3.750 -0.2775 0.01364 0.00529 0.0134 0.4774 0.0078 -3.500 -0.2522 0.01332 0.00490 0.0140 0.4699 0.0081 -3.250 -0.2267 0.01304 0.00455 0.0145 0.4630 0.0087 -3.000 -0.2013 0.01277 0.00422 0.0150 0.4556 0.0092 -2.750 -0.1758 0.01254 0.00394 0.0155 0.4491 0.0102 -2.500 -0.1499 0.01234 0.00370 0.0160 0.4429 0.0114 -2.250 -0.1243 0.01214 0.00347 0.0165 0.4369 0.0140 -2.000 -0.0987 0.01193 0.00328 0.0170 0.4317 0.0213 -1.750 -0.0733 0.01170 0.00311 0.0174 0.4261 0.0383 -1.500 -0.0483 0.01149 0.00297 0.0180 0.4204 0.0659 -1.250 -0.0243 0.01118 0.00285 0.0186 0.4153 0.1213 -1.000 -0.0152 0.00979 0.00257 0.0216 0.4110 0.4237 -0.750 -0.0185 0.00852 0.00304 0.0289 0.4075 0.8527 -0.500 0.0030 0.00878 0.00322 0.0306 0.4031 0.8788 -0.250 0.0272 0.00903 0.00340 0.0317 0.3992 0.8916 0.000 0.0592 0.00955 0.00388 0.0316 0.3945 0.9006 0.250 0.0847 0.00985 0.00410 0.0326 0.3899 0.9092 0.500 0.1216 0.01034 0.00451 0.0314 0.3853 0.9141 0.750 0.1503 0.01049 0.00461 0.0314 0.3814 0.9181 1.000 0.1724 0.01046 0.00452 0.0325 0.3778 0.9209 1.250 0.1956 0.01044 0.00444 0.0333 0.3742 0.9231 1.500 0.2238 0.01049 0.00442 0.0332 0.3705 0.9238 1.750 0.2524 0.01051 0.00440 0.0330 0.3670 0.9245 2.000 0.2808 0.01055 0.00440 0.0328 0.3634 0.9252 2.250 0.3086 0.01059 0.00440 0.0328 0.3600 0.9259 2.500 0.3360 0.01065 0.00441 0.0327 0.3566 0.9268 2.750 0.3635 0.01070 0.00443 0.0327 0.3534 0.9277 3.000 0.3906 0.01073 0.00444 0.0327 0.3504 0.9286 3.250 0.4173 0.01076 0.00446 0.0329 0.3474 0.9296 3.500 0.4436 0.01082 0.00449 0.0330 0.3444 0.9308 3.750 0.4691 0.01088 0.00451 0.0333 0.3413 0.9320 4.000 0.4944 0.01092 0.00455 0.0337 0.3384 0.9331 4.250 0.5199 0.01094 0.00457 0.0340 0.3356 0.9342 4.500 0.5450 0.01097 0.00460 0.0343 0.3324 0.9355 4.750 0.5697 0.01102 0.00464 0.0348 0.3292 0.9369 5.000 0.5952 0.01109 0.00470 0.0350 0.3264 0.9378 5.250 0.6220 0.01118 0.00478 0.0350 0.3236 0.9383 5.500 0.6494 0.01123 0.00486 0.0349 0.3207 0.9388 5.750 0.6765 0.01130 0.00496 0.0348 0.3174 0.9393 6.000 0.7033 0.01139 0.00506 0.0347 0.3140 0.9399 6.250 0.7296 0.01151 0.00516 0.0348 0.3108 0.9406 6.500 0.7560 0.01162 0.00530 0.0348 0.3079 0.9412 6.750 0.7828 0.01170 0.00543 0.0347 0.3045 0.9421 7.000 0.8091 0.01180 0.00556 0.0348 0.3006 0.9430 7.250 0.8350 0.01193 0.00570 0.0348 0.2968 0.9438 7.500 0.8605 0.01207 0.00585 0.0349 0.2932 0.9446 7.750 0.8869 0.01216 0.00600 0.0349 0.2894 0.9455 8.000 0.9127 0.01228 0.00616 0.0349 0.2851 0.9463 8.250 0.9378 0.01244 0.00633 0.0350 0.2804 0.9473 8.500 0.9636 0.01258 0.00651 0.0350 0.2759 0.9482 8.750 0.9893 0.01272 0.00671 0.0350 0.2709 0.9491 9.000 1.0140 0.01293 0.00691 0.0351 0.2651 0.9500 9.250 1.0399 0.01309 0.00713 0.0350 0.2591 0.9508 9.500 1.0644 0.01331 0.00738 0.0351 0.2525 0.9516 9.750 1.0887 0.01352 0.00764 0.0353 0.2460 0.9524 10.000 1.1117 0.01380 0.00793 0.0356 0.2377 0.9534 10.250 1.1350 0.01407 0.00824 0.0359 0.2296 0.9545 10.500 1.1570 0.01442 0.00860 0.0363 0.2212 0.9557 10.750 1.1785 0.01480 0.00900 0.0367 0.2107 0.9569 11.000 1.1994 0.01521 0.00943 0.0372 0.2003 0.9582 11.250 1.2189 0.01570 0.00993 0.0378 0.1896 0.9597 11.500 1.2368 0.01630 0.01052 0.0385 0.1772 0.9613 11.750 1.2522 0.01697 0.01118 0.0395 0.1646 0.9630 12.000 1.2629 0.01768 0.01189 0.0412 0.1537 0.9650 12.250 1.2730 0.01856 0.01277 0.0428 0.1422 0.9676 12.500 1.2822 0.01958 0.01382 0.0440 0.1313 0.9705 12.750 1.2894 0.02083 0.01509 0.0450 0.1214 0.9735 13.000 1.2944 0.02241 0.01670 0.0456 0.1125 0.9774 13.250 1.2986 0.02443 0.01876 0.0454 0.1042 0.9816 13.500 1.3038 0.02663 0.02101 0.0446 0.0964 0.9869 13.750 1.3060 0.02939 0.02382 0.0433 0.0893 0.9922 14.000 1.3070 0.03254 0.02703 0.0415 0.0824 0.9962 14.250 1.3044 0.03572 0.03028 0.0401 0.0776 1.0000 14.500 1.2993 0.03919 0.03382 0.0390 0.0729 1.0000 14.750 1.2915 0.04303 0.03773 0.0377 0.0692 1.0000 15.000 1.2855 0.04666 0.04143 0.0365 0.0654 1.0000 15.250 1.2752 0.05080 0.04563 0.0352 0.0619 1.0000 15.500 1.2648 0.05496 0.04986 0.0339 0.0589 1.0000 15.750 1.2569 0.05895 0.05392 0.0326 0.0556 1.0000 16.000 1.2467 0.06331 0.05833 0.0312 0.0524 1.0000 16.250 1.2377 0.06761 0.06269 0.0297 0.0496 1.0000 16.500 1.2303 0.07173 0.06688 0.0282 0.0468 1.0000 16.750 1.2213 0.07613 0.07133 0.0267 0.0442 1.0000 17.000 1.2135 0.08044 0.07569 0.0252 0.0418 1.0000 17.250 1.2085 0.08437 0.07969 0.0237 0.0395 1.0000 17.500 1.2008 0.08872 0.08410 0.0221 0.0373 1.0000