EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 100,000 Max Cl/Cd: 35.58 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh0009-il-100000-n5.txt Download as CSV file: xf-eh0009-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 0.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7160 0.08465 0.07983 -0.0064 1.0000 0.0176
-10.500 -0.7347 0.07534 0.07049 -0.0136 1.0000 0.0173
-10.250 -0.7535 0.06806 0.06311 -0.0197 1.0000 0.0170
-10.000 -0.7733 0.06236 0.05727 -0.0235 1.0000 0.0169
-9.750 -0.7922 0.05798 0.05272 -0.0245 1.0000 0.0168
-9.500 -0.8085 0.05430 0.04883 -0.0233 1.0000 0.0167
-9.250 -0.8186 0.05034 0.04456 -0.0222 1.0000 0.0168
-9.000 -0.8233 0.04635 0.04017 -0.0208 1.0000 0.0169
-8.750 -0.8220 0.04264 0.03602 -0.0192 1.0000 0.0172
-8.500 -0.8153 0.03928 0.03218 -0.0176 1.0000 0.0178
-8.250 -0.8026 0.03697 0.02935 -0.0161 1.0000 0.0190
-8.000 -0.7920 0.03356 0.02569 -0.0149 1.0000 0.0206
-7.750 -0.7755 0.03147 0.02339 -0.0138 1.0000 0.0222
-7.500 -0.7569 0.02924 0.02087 -0.0126 1.0000 0.0234
-7.250 -0.7372 0.02721 0.01859 -0.0114 1.0000 0.0250
-7.000 -0.7171 0.02542 0.01657 -0.0101 1.0000 0.0270
-6.750 -0.6981 0.02382 0.01476 -0.0088 1.0000 0.0305
-6.500 -0.6784 0.02263 0.01351 -0.0077 1.0000 0.0355
-6.250 -0.6584 0.02141 0.01208 -0.0063 1.0000 0.0400
-6.000 -0.6395 0.02019 0.01087 -0.0051 1.0000 0.0490
-5.750 -0.6198 0.01907 0.00973 -0.0038 1.0000 0.0622
-5.500 -0.6004 0.01795 0.00871 -0.0025 1.0000 0.0857
-5.250 -0.5806 0.01694 0.00791 -0.0014 1.0000 0.1272
-5.000 -0.5604 0.01609 0.00727 -0.0003 1.0000 0.1756
-4.750 -0.5408 0.01528 0.00671 0.0008 1.0000 0.2416
-4.500 -0.5207 0.01463 0.00628 0.0020 1.0000 0.3007
-4.250 -0.5001 0.01410 0.00591 0.0032 1.0000 0.3537
-4.000 -0.4794 0.01363 0.00559 0.0045 1.0000 0.4052
-3.750 -0.4586 0.01323 0.00533 0.0059 1.0000 0.4545
-3.500 -0.4376 0.01288 0.00510 0.0072 1.0000 0.5010
-3.250 -0.4167 0.01258 0.00487 0.0087 1.0000 0.5450
-3.000 -0.3957 0.01233 0.00473 0.0102 1.0000 0.5870
-2.750 -0.3747 0.01212 0.00461 0.0117 1.0000 0.6268
-2.500 -0.3537 0.01196 0.00453 0.0133 1.0000 0.6652
-2.250 -0.3327 0.01184 0.00448 0.0148 1.0000 0.7014
-2.000 -0.3115 0.01175 0.00443 0.0164 1.0000 0.7367
-1.750 -0.2905 0.01171 0.00444 0.0180 1.0000 0.7702
-1.500 -0.2665 0.01170 0.00447 0.0189 0.9982 0.8030
-1.250 -0.2268 0.01177 0.00455 0.0167 0.9883 0.8339
-1.000 -0.1850 0.01185 0.00461 0.0141 0.9791 0.8619
-0.750 -0.1412 0.01193 0.00468 0.0111 0.9697 0.8864
-0.500 -0.0952 0.01199 0.00473 0.0077 0.9599 0.9060
-0.250 -0.0478 0.01203 0.00475 0.0039 0.9496 0.9233
0.000 0.0000 0.01204 0.00476 0.0000 0.9376 0.9377
0.250 0.0478 0.01203 0.00475 -0.0039 0.9233 0.9496
0.500 0.0952 0.01199 0.00473 -0.0077 0.9061 0.9599
0.750 0.1411 0.01193 0.00468 -0.0111 0.8864 0.9697
1.000 0.1850 0.01185 0.00461 -0.0141 0.8619 0.9791
1.250 0.2268 0.01177 0.00455 -0.0167 0.8340 0.9884
1.500 0.2665 0.01170 0.00447 -0.0189 0.8030 0.9983
1.750 0.2903 0.01171 0.00444 -0.0179 0.7701 1.0000
2.000 0.3113 0.01175 0.00443 -0.0163 0.7367 1.0000
2.250 0.3325 0.01184 0.00448 -0.0148 0.7016 1.0000
2.500 0.3535 0.01196 0.00453 -0.0132 0.6651 1.0000
2.750 0.3744 0.01212 0.00461 -0.0117 0.6270 1.0000
3.000 0.3955 0.01233 0.00473 -0.0101 0.5870 1.0000
3.250 0.4164 0.01258 0.00487 -0.0087 0.5452 1.0000
3.500 0.4374 0.01288 0.00510 -0.0072 0.5011 1.0000
3.750 0.4584 0.01322 0.00533 -0.0058 0.4547 1.0000
4.000 0.4792 0.01363 0.00559 -0.0045 0.4056 1.0000
4.250 0.4999 0.01409 0.00591 -0.0032 0.3539 1.0000
4.500 0.5205 0.01463 0.00628 -0.0019 0.3006 1.0000
4.750 0.5407 0.01528 0.00671 -0.0007 0.2418 1.0000
5.000 0.5603 0.01609 0.00727 0.0004 0.1760 1.0000
5.250 0.5805 0.01694 0.00791 0.0014 0.1271 1.0000
5.500 0.6003 0.01794 0.00871 0.0025 0.0859 1.0000
5.750 0.6198 0.01907 0.00972 0.0038 0.0622 1.0000
6.000 0.6394 0.02019 0.01087 0.0051 0.0490 1.0000
6.250 0.6584 0.02141 0.01208 0.0063 0.0400 1.0000
6.500 0.6785 0.02263 0.01351 0.0077 0.0355 1.0000
6.750 0.6981 0.02382 0.01476 0.0088 0.0304 1.0000
7.000 0.7172 0.02543 0.01658 0.0100 0.0270 1.0000
7.250 0.7373 0.02721 0.01859 0.0113 0.0250 1.0000
7.500 0.7570 0.02923 0.02087 0.0126 0.0234 1.0000
7.750 0.7756 0.03149 0.02340 0.0138 0.0221 1.0000
8.000 0.7922 0.03357 0.02570 0.0149 0.0206 1.0000
8.250 0.8030 0.03687 0.02927 0.0161 0.0189 1.0000
8.500 0.8156 0.03929 0.03219 0.0176 0.0178 1.0000
8.750 0.8223 0.04265 0.03604 0.0191 0.0172 1.0000
9.000 0.8235 0.04642 0.04025 0.0207 0.0169 1.0000
9.250 0.8192 0.05034 0.04456 0.0221 0.0168 1.0000
9.500 0.8091 0.05433 0.04886 0.0232 0.0167 1.0000
9.750 0.7924 0.05806 0.05280 0.0243 0.0167 1.0000
10.000 0.7732 0.06251 0.05743 0.0232 0.0168 1.0000
10.250 0.7549 0.06800 0.06305 0.0196 0.0171 1.0000
10.500 0.7350 0.07555 0.07070 0.0133 0.0173 1.0000
10.750 0.7165 0.08486 0.08004 0.0061 0.0176 1.0000
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Polar data table (+)
Polar graphs
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