XFOIL Version 6.96 Calculated polar for: EPPLER EA 8(-1)-006 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.6915 0.08963 0.08614 0.0026 1.0000 0.0115 -9.500 -0.6986 0.08392 0.08049 -0.0009 1.0000 0.0116 -9.250 -0.7155 0.07603 0.07267 -0.0070 1.0000 0.0112 -9.000 -0.7421 0.06733 0.06395 -0.0130 1.0000 0.0109 -8.750 -0.7640 0.05799 0.05443 -0.0161 1.0000 0.0105 -8.500 -0.7780 0.04982 0.04593 -0.0168 1.0000 0.0105 -8.250 -0.7828 0.04337 0.03908 -0.0162 1.0000 0.0107 -8.000 -0.7745 0.03988 0.03528 -0.0153 1.0000 0.0113 -7.750 -0.7601 0.03773 0.03289 -0.0145 1.0000 0.0124 -7.500 -0.7514 0.03303 0.02767 -0.0129 1.0000 0.0135 -7.250 -0.7457 0.02572 0.01941 -0.0101 1.0000 0.0146 -7.000 -0.7291 0.02183 0.01487 -0.0083 1.0000 0.0161 -6.750 -0.7082 0.01982 0.01252 -0.0071 1.0000 0.0177 -6.500 -0.6837 0.01988 0.01259 -0.0067 1.0000 0.0203 -6.250 -0.6590 0.01991 0.01248 -0.0061 1.0000 0.0242 -5.750 -0.6108 0.01921 0.01134 -0.0046 1.0000 0.0341 -5.500 -0.5870 0.01935 0.01129 -0.0039 1.0000 0.0388 -5.250 -0.5636 0.01914 0.01103 -0.0032 1.0000 0.0421 -5.000 -0.5406 0.01864 0.01035 -0.0024 1.0000 0.0465 -4.750 -0.5175 0.01794 0.00960 -0.0017 1.0000 0.0494 -4.500 -0.4941 0.01734 0.00883 -0.0008 1.0000 0.0525 -4.250 -0.4705 0.01668 0.00804 0.0001 1.0000 0.0538 -4.000 -0.4469 0.01610 0.00735 0.0010 1.0000 0.0548 -3.750 -0.4236 0.01554 0.00674 0.0020 1.0000 0.0556 -3.500 -0.4013 0.01474 0.00603 0.0029 1.0000 0.0571 -3.250 -0.3789 0.01420 0.00549 0.0039 1.0000 0.0585 -3.000 -0.3567 0.01372 0.00503 0.0050 1.0000 0.0594 -2.750 -0.3348 0.01329 0.00461 0.0061 1.0000 0.0603 -2.500 -0.3129 0.01291 0.00425 0.0072 1.0000 0.0613 -2.250 -0.2909 0.01262 0.00396 0.0083 1.0000 0.0627 -2.000 -0.2697 0.01222 0.00360 0.0094 1.0000 0.0641 -1.750 -0.2480 0.01193 0.00334 0.0105 1.0000 0.0654 -1.500 -0.2045 0.01164 0.00307 0.0070 0.9905 0.0672 -1.250 -0.1592 0.01136 0.00280 0.0032 0.9777 0.0698 -1.000 -0.1168 0.01106 0.00253 0.0002 0.9618 0.0734 -0.750 -0.0726 0.01079 0.00228 -0.0030 0.9310 0.0775 -0.500 -0.0333 0.01052 0.00202 -0.0050 0.8778 0.0884 -0.250 -0.0075 0.00991 0.00181 -0.0043 0.7928 0.2521 0.000 0.0000 0.00902 0.00157 0.0000 0.5977 0.5973 0.250 0.0075 0.00990 0.00181 0.0043 0.2529 0.7936 0.500 0.0333 0.01052 0.00202 0.0050 0.0884 0.8776 0.750 0.0724 0.01078 0.00228 0.0031 0.0775 0.9307 1.000 0.1167 0.01106 0.00253 -0.0001 0.0734 0.9617 1.250 0.1590 0.01136 0.00280 -0.0032 0.0698 0.9776 1.500 0.2039 0.01164 0.00307 -0.0069 0.0672 0.9902 1.750 0.2480 0.01193 0.00334 -0.0105 0.0654 1.0000 2.000 0.2697 0.01222 0.00360 -0.0094 0.0640 1.0000 2.250 0.2909 0.01262 0.00396 -0.0083 0.0627 1.0000 2.500 0.3129 0.01292 0.00425 -0.0072 0.0614 1.0000 2.750 0.3347 0.01329 0.00461 -0.0061 0.0603 1.0000 3.000 0.3567 0.01372 0.00503 -0.0050 0.0594 1.0000 3.250 0.3789 0.01420 0.00549 -0.0039 0.0585 1.0000 3.500 0.4012 0.01474 0.00603 -0.0029 0.0571 1.0000 3.750 0.4235 0.01553 0.00673 -0.0020 0.0556 1.0000 4.000 0.4468 0.01610 0.00735 -0.0010 0.0548 1.0000 4.250 0.4704 0.01668 0.00804 -0.0001 0.0539 1.0000 4.500 0.4940 0.01733 0.00883 0.0008 0.0525 1.0000 4.750 0.5174 0.01794 0.00960 0.0017 0.0494 1.0000 5.000 0.5405 0.01864 0.01035 0.0024 0.0465 1.0000 5.250 0.5635 0.01913 0.01102 0.0032 0.0421 1.0000 5.500 0.5869 0.01937 0.01132 0.0039 0.0389 1.0000 5.750 0.6108 0.01919 0.01132 0.0046 0.0341 1.0000 6.250 0.6590 0.01988 0.01244 0.0061 0.0241 1.0000 6.500 0.6836 0.01989 0.01260 0.0067 0.0203 1.0000 6.750 0.7082 0.01981 0.01250 0.0071 0.0177 1.0000 7.000 0.7290 0.02182 0.01486 0.0083 0.0161 1.0000 7.250 0.7457 0.02569 0.01938 0.0101 0.0146 1.0000 7.500 0.7515 0.03296 0.02759 0.0129 0.0135 1.0000 7.750 0.7592 0.03797 0.03314 0.0146 0.0124 1.0000 8.000 0.7697 0.04129 0.03680 0.0156 0.0115 1.0000 8.250 0.7817 0.04364 0.03937 0.0162 0.0107 1.0000 8.500 0.7766 0.05018 0.04631 0.0168 0.0105 1.0000 8.750 0.7652 0.05762 0.05405 0.0162 0.0105 1.0000 9.000 0.7434 0.06700 0.06362 0.0131 0.0108 1.0000 9.250 0.7146 0.07630 0.07293 0.0068 0.0113 1.0000 9.500 0.6922 0.08571 0.08225 -0.0002 0.0124 1.0000