AS5045 (15%) (as5045-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AS5045 (15%) (as5045-il) Reynolds number: 50,000 Max Cl/Cd: 29.97 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-as5045-il-50000.txt Download as CSV file: xf-as5045-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AS5045 (15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4600 0.11981 0.11326 -0.0016 1.0000 0.3107
-10.000 -0.5796 0.08871 0.08237 -0.0349 1.0000 0.1401
-9.750 -0.6195 0.07983 0.07348 -0.0416 1.0000 0.1309
-9.500 -0.6578 0.07355 0.06715 -0.0447 1.0000 0.1257
-9.250 -0.6941 0.06850 0.06174 -0.0462 1.0000 0.1192
-9.000 -0.6931 0.06402 0.05717 -0.0462 1.0000 0.1156
-8.750 -0.7053 0.05962 0.05240 -0.0457 1.0000 0.1108
-8.500 -0.7190 0.05693 0.04904 -0.0436 1.0000 0.1061
-8.250 -0.7165 0.05401 0.04607 -0.0414 1.0000 0.1047
-8.000 -0.7200 0.05178 0.04369 -0.0382 1.0000 0.1033
-7.750 -0.7207 0.04952 0.04120 -0.0353 1.0000 0.1017
-7.500 -0.7167 0.04710 0.03844 -0.0328 1.0000 0.0996
-7.250 -0.7083 0.04468 0.03561 -0.0307 1.0000 0.0976
-7.000 -0.6957 0.04244 0.03293 -0.0288 1.0000 0.0960
-6.750 -0.6796 0.04045 0.03056 -0.0272 1.0000 0.0953
-6.500 -0.6606 0.03860 0.02850 -0.0256 1.0000 0.0955
-6.250 -0.6398 0.03695 0.02674 -0.0240 1.0000 0.0966
-6.000 -0.6186 0.03564 0.02539 -0.0223 1.0000 0.0999
-5.750 -0.5969 0.03468 0.02432 -0.0203 1.0000 0.1047
-5.500 -0.5757 0.03376 0.02349 -0.0177 1.0000 0.1104
-5.250 -0.5592 0.03294 0.02269 -0.0152 1.0000 0.1171
-5.000 -0.5461 0.03191 0.02172 -0.0129 1.0000 0.1259
-4.750 -0.5336 0.03057 0.02052 -0.0114 1.0000 0.1432
-4.250 -0.5307 0.03022 0.02345 0.0014 1.0000 0.6339
-4.000 -0.4096 0.04476 0.03733 0.0255 1.0000 0.8291
-3.750 -0.3863 0.04386 0.03615 0.0251 1.0000 0.8494
-3.500 -0.3690 0.04297 0.03504 0.0254 1.0000 0.8674
-3.250 -0.3479 0.04212 0.03395 0.0249 1.0000 0.8840
-3.000 -0.3207 0.04129 0.03290 0.0233 1.0000 0.8994
-2.750 -0.2892 0.04051 0.03189 0.0208 1.0000 0.9133
-2.500 -0.2590 0.03979 0.03097 0.0182 1.0000 0.9255
-2.250 -0.2358 0.03917 0.03019 0.0168 1.0000 0.9359
-2.000 -0.2253 0.03869 0.02960 0.0175 1.0000 0.9452
-1.750 -0.1906 0.03821 0.02894 0.0138 1.0000 0.9542
-1.500 -0.1703 0.03784 0.02846 0.0127 1.0000 0.9619
-1.250 -0.1460 0.03757 0.02808 0.0107 1.0000 0.9695
-1.000 -0.1211 0.03736 0.02778 0.0086 1.0000 0.9762
-0.750 -0.0989 0.03726 0.02758 0.0070 1.0000 0.9826
-0.500 -0.0719 0.03723 0.02748 0.0044 1.0000 0.9886
-0.250 -0.0267 0.03739 0.02755 -0.0017 0.9945 0.9941
0.000 0.0257 0.03758 0.02767 -0.0092 0.9865 0.9991
0.250 0.0572 0.03779 0.02783 -0.0126 0.9783 1.0000
0.500 0.0874 0.03808 0.02808 -0.0157 0.9698 1.0000
0.750 0.1128 0.03836 0.02836 -0.0178 0.9606 1.0000
1.000 0.1345 0.03870 0.02870 -0.0192 0.9510 1.0000
1.250 0.1628 0.03916 0.02915 -0.0217 0.9409 1.0000
1.500 0.1920 0.03965 0.02966 -0.0242 0.9297 1.0000
1.750 0.2069 0.04013 0.03016 -0.0242 0.9181 1.0000
2.000 0.2283 0.04071 0.03077 -0.0252 0.9059 1.0000
2.250 0.2552 0.04136 0.03146 -0.0269 0.8928 1.0000
2.500 0.2858 0.04205 0.03220 -0.0291 0.8787 1.0000
2.750 0.3120 0.04273 0.03294 -0.0305 0.8640 1.0000
3.000 0.3281 0.04342 0.03369 -0.0301 0.8485 1.0000
3.250 0.3502 0.04413 0.03448 -0.0304 0.8321 1.0000
3.500 0.3787 0.04487 0.03529 -0.0315 0.8150 1.0000
3.750 0.3869 0.04558 0.03606 -0.0296 0.7974 1.0000
4.000 0.3926 0.04629 0.03684 -0.0272 0.7792 1.0000
4.250 0.4016 0.04696 0.03758 -0.0252 0.7604 1.0000
4.500 0.4186 0.04757 0.03827 -0.0241 0.7411 1.0000
4.750 0.4531 0.04798 0.03880 -0.0249 0.7215 1.0000
5.000 0.4751 0.04840 0.03932 -0.0240 0.7021 1.0000
5.250 0.4741 0.04907 0.04006 -0.0208 0.6817 1.0000
5.500 0.5016 0.04933 0.04044 -0.0207 0.6610 1.0000
5.750 0.5497 0.04884 0.04014 -0.0219 0.6414 1.0000
6.000 0.5620 0.04938 0.04078 -0.0206 0.6193 1.0000
6.250 0.6017 0.04863 0.04021 -0.0208 0.5985 1.0000
6.500 0.6622 0.04615 0.03799 -0.0210 0.5803 1.0000
6.750 0.6796 0.04620 0.03817 -0.0198 0.5560 1.0000
7.000 0.7381 0.04251 0.03474 -0.0185 0.5373 1.0000
7.250 0.8066 0.03744 0.02986 -0.0171 0.5173 1.0000
7.500 0.8642 0.03357 0.02605 -0.0159 0.4883 1.0000
7.750 0.9018 0.03210 0.02448 -0.0148 0.4525 1.0000
8.000 0.9335 0.03182 0.02402 -0.0140 0.4144 1.0000
8.250 0.9653 0.03221 0.02409 -0.0138 0.3777 1.0000
8.500 0.9903 0.03338 0.02507 -0.0136 0.3446 1.0000
8.750 1.0146 0.03477 0.02632 -0.0135 0.3145 1.0000
9.000 1.0339 0.03658 0.02820 -0.0134 0.2887 1.0000
9.250 1.0606 0.03828 0.02972 -0.0137 0.2650 1.0000
9.500 1.0795 0.04042 0.03201 -0.0137 0.2454 1.0000
9.750 1.1002 0.04269 0.03438 -0.0138 0.2283 1.0000
10.000 1.1195 0.04514 0.03694 -0.0138 0.2137 1.0000
10.250 1.1388 0.04777 0.03966 -0.0138 0.2014 1.0000
10.500 1.1641 0.05035 0.04217 -0.0143 0.1896 1.0000
10.750 1.1574 0.05399 0.04641 -0.0127 0.1835 1.0000
11.000 1.1835 0.05681 0.04914 -0.0132 0.1744 1.0000
11.250 1.1657 0.06112 0.05400 -0.0112 0.1719 1.0000
11.500 1.1434 0.06567 0.05893 -0.0095 0.1702 1.0000
11.750 1.1126 0.07071 0.06425 -0.0082 0.1700 1.0000
12.000 1.0740 0.07733 0.07108 -0.0089 0.1712 1.0000
12.250 1.0318 0.08561 0.07950 -0.0116 0.1731 1.0000
12.500 0.9931 0.09505 0.08902 -0.0154 0.1747 1.0000
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Polar data table (+)
Polar graphs
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