XFOIL Version 6.96 Calculated polar for: EPPLER 344 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.1274 0.09068 0.08715 -0.0559 0.6307 0.0129 -10.250 -0.1229 0.08759 0.08402 -0.0567 0.6212 0.0129 -10.000 -0.1265 0.08262 0.07904 -0.0587 0.6149 0.0130 -9.750 -0.1293 0.07792 0.07432 -0.0606 0.6087 0.0130 -9.500 -0.1291 0.07403 0.07041 -0.0619 0.6009 0.0130 -9.000 -0.1385 0.06437 0.06074 -0.0660 0.5895 0.0130 -8.750 -0.1425 0.06005 0.05641 -0.0681 0.5831 0.0130 -8.250 -0.1687 0.05016 0.04646 -0.0744 0.5741 0.0130 -7.750 -0.2355 0.05714 0.05314 -0.0736 0.5770 0.0098 -7.500 -0.2393 0.05373 0.04963 -0.0722 0.5700 0.0098 -7.250 -0.2404 0.05035 0.04610 -0.0705 0.5631 0.0098 -7.000 -0.2374 0.04744 0.04305 -0.0688 0.5560 0.0094 -6.750 -0.2336 0.04413 0.03956 -0.0667 0.5488 0.0094 -6.500 -0.2279 0.04078 0.03598 -0.0644 0.5419 0.0095 -6.250 -0.2211 0.03688 0.03182 -0.0616 0.5359 0.0098 -6.000 -0.2112 0.03397 0.02867 -0.0592 0.5292 0.0097 -5.500 -0.2044 0.02090 0.01413 -0.0496 0.5210 0.0081 -5.250 -0.1830 0.01928 0.01215 -0.0482 0.5139 0.0080 -5.000 -0.1600 0.01809 0.01070 -0.0472 0.5075 0.0080 -4.750 -0.1359 0.01706 0.00947 -0.0463 0.5006 0.0080 -4.250 -0.0866 0.01555 0.00765 -0.0449 0.4871 0.0081 -4.000 -0.0619 0.01497 0.00696 -0.0442 0.4803 0.0083 -3.750 -0.0373 0.01447 0.00637 -0.0435 0.4744 0.0083 -3.500 -0.0126 0.01402 0.00586 -0.0428 0.4685 0.0085 -3.250 0.0118 0.01365 0.00542 -0.0421 0.4628 0.0086 -3.000 0.0362 0.01330 0.00501 -0.0413 0.4579 0.0090 -2.750 0.0607 0.01299 0.00465 -0.0406 0.4528 0.0093 -2.500 0.0851 0.01273 0.00433 -0.0398 0.4475 0.0095 -2.250 0.1097 0.01251 0.00404 -0.0391 0.4428 0.0102 -2.000 0.1345 0.01227 0.00378 -0.0384 0.4378 0.0107 -1.750 0.1594 0.01210 0.00357 -0.0378 0.4330 0.0117 -1.500 0.1844 0.01198 0.00339 -0.0372 0.4287 0.0128 -1.250 0.2098 0.01183 0.00323 -0.0366 0.4250 0.0152 -1.000 0.2352 0.01170 0.00311 -0.0361 0.4211 0.0197 -0.750 0.2602 0.01156 0.00300 -0.0355 0.4171 0.0314 -0.500 0.2849 0.01144 0.00293 -0.0349 0.4133 0.0543 -0.250 0.3094 0.01125 0.00288 -0.0343 0.4097 0.0997 0.000 0.3176 0.00980 0.00272 -0.0312 0.4068 0.5038 0.250 0.3178 0.00905 0.00324 -0.0247 0.4040 0.8678 0.500 0.3399 0.00931 0.00344 -0.0230 0.4008 0.8908 0.750 0.3632 0.00959 0.00367 -0.0216 0.3977 0.9009 1.000 0.3861 0.00980 0.00382 -0.0202 0.3950 0.9100 1.250 0.4077 0.01004 0.00404 -0.0183 0.3923 0.9213 1.500 0.4330 0.01022 0.00420 -0.0173 0.3892 0.9273 1.750 0.4592 0.01028 0.00419 -0.0170 0.3859 0.9289 2.000 0.4850 0.01033 0.00418 -0.0167 0.3829 0.9302 2.250 0.5105 0.01040 0.00418 -0.0163 0.3803 0.9314 2.500 0.5367 0.01043 0.00418 -0.0161 0.3781 0.9326 2.750 0.5627 0.01047 0.00419 -0.0158 0.3753 0.9339 3.000 0.5888 0.01051 0.00421 -0.0156 0.3725 0.9350 3.250 0.6148 0.01057 0.00423 -0.0154 0.3697 0.9359 3.500 0.6408 0.01065 0.00427 -0.0152 0.3673 0.9368 3.750 0.6666 0.01074 0.00431 -0.0150 0.3649 0.9376 4.000 0.6931 0.01080 0.00437 -0.0149 0.3626 0.9384 4.250 0.7195 0.01086 0.00444 -0.0147 0.3601 0.9393 4.500 0.7458 0.01093 0.00451 -0.0146 0.3575 0.9400 4.750 0.7719 0.01102 0.00459 -0.0145 0.3550 0.9408 5.000 0.7975 0.01112 0.00467 -0.0142 0.3523 0.9416 5.250 0.8227 0.01124 0.00477 -0.0140 0.3499 0.9425 5.500 0.8485 0.01134 0.00488 -0.0138 0.3478 0.9434 5.750 0.8746 0.01142 0.00498 -0.0137 0.3454 0.9443 6.000 0.9003 0.01152 0.00510 -0.0135 0.3426 0.9453 6.250 0.9256 0.01162 0.00522 -0.0133 0.3400 0.9464 6.500 0.9502 0.01175 0.00535 -0.0130 0.3373 0.9477 6.750 0.9745 0.01190 0.00549 -0.0126 0.3346 0.9489 7.000 0.9997 0.01203 0.00564 -0.0124 0.3322 0.9499 7.250 1.0252 0.01214 0.00580 -0.0123 0.3294 0.9508 7.500 1.0498 0.01225 0.00596 -0.0120 0.3265 0.9517 7.750 1.0737 0.01239 0.00611 -0.0115 0.3233 0.9527 8.000 1.0968 0.01255 0.00628 -0.0110 0.3205 0.9539 8.250 1.1201 0.01271 0.00648 -0.0105 0.3173 0.9551 8.500 1.1441 0.01284 0.00667 -0.0101 0.3141 0.9564 8.750 1.1671 0.01299 0.00686 -0.0096 0.3104 0.9579 9.000 1.1888 0.01316 0.00707 -0.0089 0.3069 0.9595 9.250 1.2087 0.01335 0.00727 -0.0078 0.3032 0.9615 9.750 1.2514 0.01369 0.00774 -0.0062 0.2954 0.9656 10.000 1.2709 0.01394 0.00801 -0.0052 0.2907 0.9680 10.250 1.2925 0.01417 0.00831 -0.0046 0.2862 0.9703 10.500 1.3130 0.01444 0.00862 -0.0039 0.2798 0.9731 10.750 1.3332 0.01479 0.00899 -0.0033 0.2747 0.9760 11.000 1.3572 0.01511 0.00938 -0.0034 0.2681 0.9785 11.250 1.3783 0.01557 0.00986 -0.0032 0.2612 0.9819 11.500 1.4015 0.01599 0.01034 -0.0035 0.2535 0.9856 11.750 1.4224 0.01656 0.01093 -0.0036 0.2450 0.9917 12.000 1.4373 0.01716 0.01156 -0.0026 0.2368 1.0000 12.250 1.4476 0.01786 0.01228 -0.0009 0.2286 1.0000 12.500 1.4544 0.01879 0.01321 0.0010 0.2197 1.0000 12.750 1.4612 0.01982 0.01425 0.0026 0.2098 1.0000 13.000 1.4665 0.02103 0.01548 0.0042 0.2013 1.0000 13.250 1.4680 0.02259 0.01705 0.0057 0.1925 1.0000 13.500 1.4706 0.02421 0.01871 0.0069 0.1839 1.0000 13.750 1.4700 0.02618 0.02071 0.0080 0.1759 1.0000 14.000 1.4662 0.02856 0.02310 0.0089 0.1678 1.0000 14.250 1.4628 0.03103 0.02562 0.0096 0.1594 1.0000 14.500 1.4562 0.03391 0.02853 0.0101 0.1531 1.0000 14.750 1.4504 0.03682 0.03149 0.0105 0.1460 1.0000 15.000 1.4391 0.04033 0.03504 0.0107 0.1394 1.0000 15.250 1.4300 0.04374 0.03850 0.0108 0.1331 1.0000 15.500 1.4166 0.04770 0.04250 0.0106 0.1273 1.0000 15.750 1.4091 0.05116 0.04603 0.0103 0.1225 1.0000 16.000 1.3961 0.05533 0.05024 0.0099 0.1174 1.0000 16.250 1.3868 0.05920 0.05418 0.0093 0.1120 1.0000 16.500 1.3746 0.06352 0.05854 0.0085 0.1067 1.0000 16.750 1.3655 0.06754 0.06261 0.0077 0.1021 1.0000 17.000 1.3562 0.07169 0.06681 0.0067 0.0973 1.0000 17.250 1.3451 0.07615 0.07130 0.0056 0.0925 1.0000 17.500 1.3377 0.08021 0.07541 0.0045 0.0876 1.0000 17.750 1.3281 0.08463 0.07986 0.0032 0.0835 1.0000 18.000 1.3232 0.08848 0.08377 0.0020 0.0793 1.0000