E226 (10.19%) (e226-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E226 (10.19%) (e226-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.82 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e226-il-1000000.txt Download as CSV file: xf-e226-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E226 (10.19%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5942 0.13873 0.13700 0.0061 1.0000 0.0114
-13.000 -0.5925 0.13404 0.13232 0.0041 1.0000 0.0115
-9.500 -0.8506 0.02772 0.02381 -0.0346 1.0000 0.0101
-9.250 -0.8348 0.02649 0.02241 -0.0332 1.0000 0.0099
-9.000 -0.8183 0.02530 0.02108 -0.0318 1.0000 0.0098
-8.750 -0.8030 0.02334 0.01902 -0.0302 1.0000 0.0095
-8.500 -0.7900 0.02133 0.01681 -0.0282 1.0000 0.0095
-8.250 -0.7752 0.01978 0.01510 -0.0262 1.0000 0.0094
-8.000 -0.7597 0.01861 0.01381 -0.0242 1.0000 0.0094
-7.750 -0.7436 0.01786 0.01294 -0.0222 1.0000 0.0096
-7.500 -0.7205 0.01710 0.01208 -0.0216 0.9992 0.0097
-7.250 -0.6895 0.01564 0.01049 -0.0228 0.9970 0.0098
-7.000 -0.6587 0.01408 0.00883 -0.0240 0.9946 0.0099
-6.750 -0.6298 0.01271 0.00738 -0.0248 0.9910 0.0104
-6.500 -0.5974 0.01194 0.00656 -0.0261 0.9880 0.0108
-6.250 -0.5634 0.01134 0.00591 -0.0277 0.9858 0.0111
-6.000 -0.5299 0.01080 0.00532 -0.0290 0.9830 0.0116
-5.750 -0.4994 0.01034 0.00481 -0.0297 0.9772 0.0120
-5.500 -0.4668 0.00991 0.00433 -0.0308 0.9725 0.0124
-5.250 -0.4385 0.00956 0.00393 -0.0309 0.9642 0.0128
-5.000 -0.4093 0.00924 0.00357 -0.0311 0.9565 0.0133
-4.750 -0.3837 0.00887 0.00313 -0.0305 0.9457 0.0149
-4.500 -0.3579 0.00860 0.00282 -0.0300 0.9349 0.0169
-4.250 -0.3331 0.00820 0.00249 -0.0293 0.9240 0.0362
-4.000 -0.3097 0.00762 0.00215 -0.0285 0.9126 0.0972
-3.750 -0.2849 0.00723 0.00194 -0.0280 0.9009 0.1458
-3.500 -0.2594 0.00693 0.00177 -0.0275 0.8893 0.1870
-3.250 -0.2339 0.00664 0.00162 -0.0271 0.8777 0.2339
-3.000 -0.2082 0.00638 0.00148 -0.0267 0.8660 0.2804
-2.750 -0.1822 0.00616 0.00137 -0.0263 0.8537 0.3234
-2.500 -0.1558 0.00597 0.00127 -0.0260 0.8411 0.3635
-2.250 -0.1299 0.00573 0.00118 -0.0256 0.8280 0.4218
-2.000 -0.1036 0.00554 0.00111 -0.0253 0.8148 0.4691
-1.750 -0.0768 0.00543 0.00105 -0.0250 0.8015 0.5016
-1.500 -0.0500 0.00533 0.00100 -0.0247 0.7877 0.5343
-1.250 -0.0231 0.00525 0.00095 -0.0245 0.7736 0.5674
-1.000 0.0037 0.00516 0.00092 -0.0242 0.7591 0.6001
-0.750 0.0305 0.00509 0.00090 -0.0239 0.7442 0.6321
-0.500 0.0573 0.00503 0.00088 -0.0236 0.7288 0.6634
-0.250 0.0840 0.00499 0.00088 -0.0233 0.7129 0.6934
0.000 0.1108 0.00495 0.00088 -0.0229 0.6966 0.7224
0.250 0.1374 0.00493 0.00089 -0.0225 0.6796 0.7510
0.500 0.1640 0.00493 0.00091 -0.0222 0.6618 0.7784
0.750 0.1904 0.00493 0.00093 -0.0217 0.6439 0.8045
1.000 0.2168 0.00494 0.00097 -0.0213 0.6255 0.8293
1.250 0.2430 0.00497 0.00101 -0.0208 0.6058 0.8535
1.500 0.2689 0.00502 0.00106 -0.0202 0.5862 0.8764
1.750 0.2949 0.00507 0.00111 -0.0197 0.5655 0.8987
2.000 0.3207 0.00515 0.00118 -0.0190 0.5443 0.9196
2.250 0.3473 0.00525 0.00125 -0.0186 0.5220 0.9390
2.500 0.3758 0.00539 0.00133 -0.0186 0.4982 0.9555
2.750 0.4075 0.00555 0.00142 -0.0194 0.4716 0.9675
3.000 0.4409 0.00572 0.00151 -0.0207 0.4458 0.9763
3.250 0.4734 0.00592 0.00161 -0.0217 0.4193 0.9844
3.500 0.5106 0.00614 0.00173 -0.0239 0.3877 0.9877
3.750 0.5456 0.00646 0.00186 -0.0256 0.3426 0.9921
4.000 0.5802 0.00680 0.00201 -0.0273 0.2969 0.9958
4.250 0.6160 0.00711 0.00218 -0.0293 0.2607 0.9990
4.500 0.6433 0.00741 0.00235 -0.0294 0.2277 1.0000
4.750 0.6641 0.00779 0.00255 -0.0282 0.1902 1.0000
5.000 0.6855 0.00815 0.00276 -0.0271 0.1578 1.0000
5.250 0.7072 0.00853 0.00301 -0.0260 0.1282 1.0000
5.500 0.7288 0.00894 0.00327 -0.0249 0.0994 1.0000
5.750 0.7506 0.00937 0.00357 -0.0239 0.0735 1.0000
6.000 0.7716 0.00990 0.00393 -0.0228 0.0443 1.0000
6.250 0.7914 0.01062 0.00446 -0.0214 0.0157 1.0000
6.500 0.8143 0.01104 0.00487 -0.0205 0.0125 1.0000
6.750 0.8380 0.01139 0.00526 -0.0197 0.0116 1.0000
7.000 0.8614 0.01179 0.00569 -0.0190 0.0107 1.0000
7.250 0.8839 0.01232 0.00627 -0.0181 0.0098 1.0000
7.500 0.9054 0.01298 0.00701 -0.0170 0.0093 1.0000
7.750 0.9283 0.01345 0.00753 -0.0162 0.0090 1.0000
8.000 0.9506 0.01399 0.00813 -0.0153 0.0089 1.0000
8.250 0.9726 0.01455 0.00875 -0.0144 0.0087 1.0000
8.500 0.9938 0.01518 0.00945 -0.0135 0.0085 1.0000
8.750 1.0145 0.01584 0.01018 -0.0124 0.0083 1.0000
9.000 1.0344 0.01658 0.01099 -0.0113 0.0081 1.0000
9.250 1.0542 0.01729 0.01175 -0.0102 0.0078 1.0000
9.500 1.0727 0.01811 0.01264 -0.0089 0.0077 1.0000
9.750 1.0905 0.01896 0.01355 -0.0076 0.0074 1.0000
10.000 1.1067 0.01993 0.01460 -0.0061 0.0073 1.0000
10.250 1.1211 0.02104 0.01579 -0.0044 0.0071 1.0000
10.500 1.1287 0.02290 0.01775 -0.0019 0.0069 1.0000
10.750 1.1403 0.02428 0.01924 0.0000 0.0069 1.0000
11.000 1.1518 0.02547 0.02053 0.0020 0.0069 1.0000
11.250 1.1510 0.02816 0.02340 0.0053 0.0067 1.0000
11.500 1.1523 0.02979 0.02521 0.0083 0.0066 1.0000
11.750 1.1555 0.03114 0.02670 0.0108 0.0066 1.0000
12.000 1.1570 0.03280 0.02850 0.0130 0.0065 1.0000
12.250 1.1564 0.03474 0.03058 0.0150 0.0065 1.0000
12.500 1.1579 0.03633 0.03232 0.0164 0.0064 1.0000
12.750 1.1514 0.03924 0.03538 0.0177 0.0065 1.0000
13.000 1.1441 0.04228 0.03860 0.0183 0.0064 1.0000
13.250 1.1367 0.04555 0.04202 0.0183 0.0064 1.0000
13.500 1.1220 0.05012 0.04678 0.0175 0.0065 1.0000
13.750 1.1158 0.05377 0.05056 0.0161 0.0064 1.0000
14.000 1.0962 0.05976 0.05673 0.0136 0.0065 1.0000
14.250 1.0815 0.06547 0.06260 0.0106 0.0065 1.0000
14.500 1.0653 0.07185 0.06913 0.0069 0.0065 1.0000
15.250 1.0224 0.09221 0.08981 -0.0050 0.0068 1.0000
15.500 1.0072 0.10013 0.09786 -0.0101 0.0068 1.0000
15.750 0.9872 0.10954 0.10739 -0.0162 0.0068 1.0000
16.000 0.9841 0.11556 0.11349 -0.0200 0.0069 1.0000
16.250 0.9648 0.12569 0.12374 -0.0262 0.0069 1.0000
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Polar data table (+)
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