EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 50,000 Max Cl/Cd: 19.74 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2010-il-50000.txt Download as CSV file: xf-eh2010-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/10
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4884 0.09749 0.09127 0.0102 1.0000 0.2821
-8.000 -0.4878 0.09450 0.08835 0.0106 1.0000 0.3024
-7.750 -0.4986 0.09212 0.08608 0.0103 1.0000 0.3189
-7.500 -0.4700 0.08772 0.08166 0.0136 1.0000 0.3534
-7.250 -0.4607 0.08456 0.07854 0.0157 1.0000 0.3848
-7.000 -0.4616 0.08213 0.07619 0.0178 1.0000 0.4173
-6.750 -0.4356 0.07815 0.07217 0.0203 1.0000 0.4550
-5.750 -0.5056 0.05117 0.04423 -0.0156 1.0000 0.1661
-5.500 -0.4899 0.04628 0.03880 -0.0152 1.0000 0.1458
-5.250 -0.4755 0.04219 0.03393 -0.0137 1.0000 0.1346
-5.000 -0.4583 0.03876 0.03021 -0.0123 1.0000 0.1329
-4.750 -0.4422 0.03607 0.02698 -0.0104 1.0000 0.1361
-4.500 -0.4244 0.03363 0.02452 -0.0089 1.0000 0.1432
-4.250 -0.4053 0.03123 0.02170 -0.0071 1.0000 0.1460
-4.000 -0.3860 0.02907 0.01912 -0.0053 1.0000 0.1512
-3.750 -0.3693 0.02754 0.01748 -0.0036 1.0000 0.1654
-3.500 -0.3515 0.02604 0.01586 -0.0019 1.0000 0.1788
-3.250 -0.3329 0.02461 0.01450 -0.0004 1.0000 0.1971
-3.000 -0.0564 0.01857 0.01058 -0.0311 1.0000 1.0000
-2.750 -0.0404 0.01836 0.01017 -0.0302 1.0000 1.0000
-2.500 -0.0284 0.01827 0.00994 -0.0289 1.0000 1.0000
-2.250 -0.0288 0.01846 0.01010 -0.0260 1.0000 1.0000
-2.000 -0.0499 0.01907 0.01071 -0.0204 1.0000 1.0000
-1.750 -0.0721 0.01969 0.01131 -0.0150 1.0000 1.0000
-1.500 -0.0637 0.02023 0.01168 -0.0146 0.9942 1.0000
-1.250 0.0153 0.02063 0.01171 -0.0258 0.9705 1.0000
-1.000 0.0898 0.02084 0.01161 -0.0357 0.9474 1.0000
-0.750 0.1708 0.02079 0.01134 -0.0461 0.9273 1.0000
-0.500 0.2258 0.02080 0.01118 -0.0515 0.9036 1.0000
-0.250 0.2699 0.02087 0.01112 -0.0546 0.8812 1.0000
0.000 0.3014 0.02108 0.01122 -0.0552 0.8590 1.0000
0.250 0.3253 0.02142 0.01146 -0.0544 0.8379 1.0000
0.500 0.3471 0.02181 0.01177 -0.0533 0.8183 1.0000
0.750 0.3692 0.02219 0.01206 -0.0520 0.8007 1.0000
1.000 0.3876 0.02272 0.01254 -0.0504 0.7828 1.0000
1.250 0.4059 0.02327 0.01306 -0.0488 0.7657 1.0000
1.500 0.4243 0.02383 0.01358 -0.0471 0.7497 1.0000
1.750 0.4426 0.02441 0.01412 -0.0454 0.7345 1.0000
2.000 0.4608 0.02503 0.01472 -0.0437 0.7197 1.0000
2.250 0.4789 0.02570 0.01540 -0.0421 0.7055 1.0000
2.500 0.4968 0.02639 0.01609 -0.0405 0.6914 1.0000
2.750 0.5145 0.02715 0.01686 -0.0389 0.6778 1.0000
3.000 0.5322 0.02794 0.01766 -0.0374 0.6643 1.0000
3.250 0.5498 0.02879 0.01854 -0.0359 0.6512 1.0000
3.500 0.5673 0.02966 0.01948 -0.0343 0.6383 1.0000
3.750 0.5850 0.03055 0.02041 -0.0328 0.6258 1.0000
4.000 0.6037 0.03139 0.02129 -0.0313 0.6139 1.0000
4.250 0.6243 0.03203 0.02196 -0.0296 0.6025 1.0000
4.500 0.6395 0.03328 0.02330 -0.0283 0.5897 1.0000
4.750 0.6544 0.03455 0.02471 -0.0270 0.5769 1.0000
5.000 0.6683 0.03599 0.02625 -0.0257 0.5644 1.0000
5.250 0.6824 0.03742 0.02778 -0.0244 0.5521 1.0000
5.500 0.6972 0.03885 0.02931 -0.0232 0.5402 1.0000
5.750 0.7147 0.04003 0.03060 -0.0218 0.5286 1.0000
6.000 0.7390 0.04053 0.03119 -0.0201 0.5177 1.0000
6.250 0.7499 0.04241 0.03327 -0.0190 0.5050 1.0000
6.500 0.7575 0.04466 0.03565 -0.0180 0.4922 1.0000
6.750 0.7619 0.04730 0.03842 -0.0171 0.4799 1.0000
7.000 0.7664 0.04989 0.04113 -0.0162 0.4676 1.0000
7.250 0.7707 0.05261 0.04395 -0.0155 0.4560 1.0000
7.500 0.7810 0.05464 0.04612 -0.0143 0.4437 1.0000
7.750 0.7965 0.05616 0.04779 -0.0129 0.4315 1.0000
8.000 0.8117 0.05759 0.04939 -0.0114 0.4183 1.0000
8.250 0.7527 0.06664 0.05820 -0.0138 0.4122 1.0000
8.500 0.7541 0.06972 0.06135 -0.0133 0.4016 1.0000
8.750 0.7631 0.07203 0.06379 -0.0124 0.3891 1.0000
9.000 0.7731 0.07427 0.06622 -0.0114 0.3762 1.0000
9.250 0.7425 0.08072 0.07249 -0.0135 0.3707 1.0000
9.500 0.7459 0.08374 0.07566 -0.0132 0.3581 1.0000
9.750 0.7506 0.08669 0.07871 -0.0128 0.3454 1.0000
10.000 0.7543 0.08960 0.08173 -0.0124 0.3311 1.0000
10.250 0.7575 0.09275 0.08497 -0.0122 0.3174 1.0000
10.500 0.7829 0.09221 0.08471 -0.0090 0.2912 1.0000
10.750 0.7805 0.09568 0.08824 -0.0090 0.2751 1.0000
11.000 1.0405 0.05270 0.04424 0.0269 0.0881 1.0000
11.250 1.0429 0.05621 0.04801 0.0283 0.0849 1.0000
11.500 1.0569 0.06027 0.05202 0.0288 0.0802 1.0000
11.750 1.0429 0.06392 0.05597 0.0299 0.0798 1.0000
12.000 1.0247 0.06814 0.06046 0.0298 0.0795 1.0000
12.250 1.0069 0.07294 0.06549 0.0287 0.0796 1.0000
12.500 0.9897 0.07824 0.07097 0.0268 0.0800 1.0000
12.750 0.9684 0.08436 0.07724 0.0238 0.0803 1.0000
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Polar data table (+)
Polar graphs
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