XFOIL Version 6.96 Calculated polar for: EPPLER 328 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.3849 0.08658 0.08443 -0.0309 1.0000 0.0150 -9.000 -0.3906 0.08173 0.07961 -0.0339 1.0000 0.0152 -8.750 -0.4050 0.07568 0.07357 -0.0389 1.0000 0.0153 -8.500 -0.4180 0.07197 0.06986 -0.0398 1.0000 0.0152 -8.250 -0.4365 0.06878 0.06665 -0.0384 1.0000 0.0152 -8.000 -0.4551 0.06620 0.06406 -0.0350 1.0000 0.0152 -7.750 -0.4674 0.06291 0.06071 -0.0325 0.9999 0.0153 -7.250 -0.4476 0.04923 0.04641 -0.0368 0.9554 0.0162 -7.000 -0.4074 0.04534 0.04241 -0.0440 0.9258 0.0166 -6.750 -0.3709 0.04191 0.03865 -0.0488 0.8745 0.0173 -6.500 -0.3594 0.03956 0.03595 -0.0469 0.8280 0.0178 -6.250 -0.3490 0.03698 0.03302 -0.0442 0.7963 0.0189 -6.000 -0.3443 0.03265 0.02805 -0.0398 0.7730 0.0205 -5.750 -0.3288 0.03102 0.02626 -0.0383 0.7509 0.0208 -5.500 -0.3121 0.02960 0.02467 -0.0369 0.7308 0.0215 -5.250 -0.2943 0.02804 0.02286 -0.0352 0.7127 0.0224 -5.000 -0.2789 0.01992 0.01342 -0.0292 0.7015 0.0127 -4.750 -0.2546 0.01795 0.01121 -0.0282 0.6856 0.0123 -4.500 -0.2295 0.01676 0.00969 -0.0272 0.6704 0.0127 -4.250 -0.2038 0.01546 0.00821 -0.0266 0.6564 0.0128 -3.750 -0.1548 0.01388 0.00646 -0.0251 0.6292 0.0136 -3.500 -0.1300 0.01360 0.00612 -0.0245 0.6159 0.0149 -3.250 -0.1057 0.01320 0.00561 -0.0236 0.6038 0.0156 -3.000 -0.0823 0.01277 0.00508 -0.0226 0.5927 0.0159 -2.750 -0.0615 0.01208 0.00436 -0.0212 0.5817 0.0168 -2.500 -0.0380 0.01175 0.00398 -0.0203 0.5710 0.0180 -2.250 -0.0149 0.01141 0.00356 -0.0192 0.5609 0.0210 -2.000 0.0081 0.01102 0.00318 -0.0181 0.5507 0.0334 -1.750 0.0293 0.01052 0.00294 -0.0169 0.5419 0.1016 -1.500 0.0340 0.00880 0.00256 -0.0133 0.5341 0.4727 -1.250 0.0372 0.00785 0.00279 -0.0079 0.5269 0.8054 -1.000 0.0599 0.00824 0.00317 -0.0059 0.5181 0.8426 -0.750 0.0835 0.00863 0.00354 -0.0042 0.5098 0.8609 -0.500 0.1075 0.00891 0.00373 -0.0028 0.5019 0.8729 -0.250 0.1316 0.00926 0.00403 -0.0012 0.4946 0.8831 0.000 0.1550 0.00963 0.00436 0.0007 0.4871 0.8939 0.250 0.1783 0.00986 0.00450 0.0020 0.4802 0.9028 0.500 0.2058 0.01010 0.00471 0.0029 0.4729 0.9085 0.750 0.2321 0.01020 0.00470 0.0033 0.4665 0.9116 1.000 0.2579 0.01015 0.00462 0.0036 0.4598 0.9137 1.250 0.2827 0.01015 0.00453 0.0040 0.4537 0.9159 1.500 0.3081 0.01014 0.00446 0.0043 0.4479 0.9178 1.750 0.3345 0.01011 0.00439 0.0045 0.4420 0.9191 2.000 0.3608 0.01016 0.00435 0.0047 0.4363 0.9203 2.250 0.3879 0.01015 0.00433 0.0047 0.4308 0.9214 2.500 0.4147 0.01017 0.00432 0.0048 0.4255 0.9226 2.750 0.4407 0.01026 0.00433 0.0050 0.4203 0.9242 3.000 0.4676 0.01025 0.00434 0.0051 0.4152 0.9257 3.250 0.4940 0.01028 0.00434 0.0052 0.4102 0.9271 3.500 0.5199 0.01037 0.00436 0.0054 0.4054 0.9287 3.750 0.5465 0.01038 0.00439 0.0054 0.4005 0.9302 4.000 0.5729 0.01042 0.00443 0.0055 0.3958 0.9320 4.250 0.5990 0.01051 0.00446 0.0056 0.3912 0.9335 4.500 0.6254 0.01055 0.00451 0.0057 0.3866 0.9347 4.750 0.6520 0.01059 0.00457 0.0058 0.3819 0.9359 5.000 0.6781 0.01067 0.00464 0.0059 0.3772 0.9373 5.250 0.7040 0.01079 0.00474 0.0061 0.3727 0.9389 5.500 0.7303 0.01083 0.00483 0.0062 0.3680 0.9405 5.750 0.7560 0.01091 0.00492 0.0064 0.3632 0.9425 6.000 0.7810 0.01107 0.00504 0.0066 0.3585 0.9447 6.250 0.8070 0.01111 0.00515 0.0067 0.3538 0.9467 6.500 0.8327 0.01118 0.00525 0.0069 0.3489 0.9484 6.750 0.8576 0.01135 0.00538 0.0072 0.3435 0.9501 7.000 0.8836 0.01138 0.00551 0.0073 0.3385 0.9521 7.250 0.9088 0.01148 0.00564 0.0075 0.3332 0.9543 7.500 0.9332 0.01166 0.00580 0.0079 0.3279 0.9568 7.750 0.9582 0.01172 0.00594 0.0081 0.3223 0.9595 8.000 0.9824 0.01184 0.00609 0.0085 0.3165 0.9622 8.250 1.0083 0.01199 0.00628 0.0085 0.3104 0.9648 8.500 1.0345 0.01212 0.00646 0.0085 0.3036 0.9677 8.750 1.0595 0.01230 0.00668 0.0086 0.2969 0.9710 9.000 1.0852 0.01245 0.00689 0.0086 0.2896 0.9743 9.250 1.1143 0.01269 0.00715 0.0077 0.2817 0.9765 9.500 1.1433 0.01292 0.00744 0.0069 0.2729 0.9791 9.750 1.1719 0.01318 0.00775 0.0061 0.2638 0.9821 10.000 1.1994 0.01351 0.00809 0.0054 0.2537 0.9854 10.250 1.2296 0.01391 0.00849 0.0041 0.2415 0.9875 10.500 1.2592 0.01433 0.00894 0.0028 0.2283 0.9901 10.750 1.2870 0.01484 0.00944 0.0018 0.2140 0.9936 11.000 1.3146 0.01543 0.01003 0.0006 0.1980 0.9982 11.250 1.3146 0.01577 0.01036 0.0050 0.1876 1.0000 11.500 1.3224 0.01628 0.01087 0.0078 0.1758 1.0000 11.750 1.3314 0.01697 0.01152 0.0100 0.1627 1.0000 12.000 1.3395 0.01778 0.01231 0.0123 0.1499 1.0000 12.250 1.3461 0.01870 0.01320 0.0145 0.1379 1.0000 12.500 1.3505 0.01978 0.01427 0.0168 0.1262 1.0000 12.750 1.3534 0.02103 0.01551 0.0189 0.1161 1.0000 13.000 1.3537 0.02257 0.01705 0.0208 0.1068 1.0000 13.250 1.3551 0.02420 0.01871 0.0222 0.0985 1.0000 13.500 1.3553 0.02610 0.02064 0.0233 0.0911 1.0000 13.750 1.3511 0.02853 0.02308 0.0241 0.0840 1.0000 14.000 1.3509 0.03080 0.02542 0.0246 0.0781 1.0000 14.250 1.3445 0.03378 0.02843 0.0248 0.0727 1.0000 14.500 1.3415 0.03656 0.03127 0.0248 0.0674 1.0000 14.750 1.3322 0.04010 0.03484 0.0245 0.0632 1.0000 15.000 1.3282 0.04316 0.03799 0.0242 0.0594 1.0000 15.250 1.3190 0.04686 0.04174 0.0237 0.0558 1.0000 15.500 1.3077 0.05090 0.04584 0.0230 0.0526 1.0000 15.750 1.3025 0.05434 0.04937 0.0222 0.0496 1.0000 16.000 1.2915 0.05859 0.05367 0.0211 0.0467 1.0000 16.250 1.2787 0.06322 0.05836 0.0199 0.0445 1.0000 16.500 1.2737 0.06697 0.06221 0.0187 0.0423 1.0000 16.750 1.2648 0.07132 0.06662 0.0173 0.0395 1.0000 17.000 1.2529 0.07619 0.07155 0.0156 0.0377 1.0000 17.250 1.2448 0.08063 0.07607 0.0140 0.0358 1.0000 17.500 1.2405 0.08460 0.08011 0.0125 0.0334 1.0000 17.750 1.2314 0.08936 0.08494 0.0106 0.0322 1.0000 18.000 1.2196 0.09460 0.09022 0.0085 0.0305 1.0000