EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 100,000 Max Cl/Cd: 46.62 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2070-il-100000.txt Download as CSV file: xf-eh2070-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/7.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4609 0.08883 0.08470 0.0049 1.0000 0.0698
-7.750 -0.4705 0.08546 0.08139 0.0009 1.0000 0.0706
-7.500 -0.4817 0.08193 0.07791 -0.0034 1.0000 0.0709
-7.250 -0.4890 0.07827 0.07418 -0.0078 1.0000 0.0713
-7.000 -0.4739 0.07145 0.06749 -0.0041 1.0000 0.0736
-6.750 -0.4661 0.06737 0.06343 -0.0033 1.0000 0.0777
-6.500 -0.5187 0.07296 0.06859 -0.0070 1.0000 0.0741
-6.250 -0.5077 0.06933 0.06495 -0.0072 1.0000 0.0781
-6.000 -0.4946 0.06791 0.06299 -0.0130 1.0000 0.0848
-5.750 -0.4843 0.06147 0.05684 -0.0110 1.0000 0.0887
-5.500 -0.4686 0.05890 0.05386 -0.0137 1.0000 0.0991
-5.250 -0.4552 0.05449 0.04968 -0.0123 1.0000 0.1062
-5.000 -0.4109 0.03670 0.03225 -0.0131 1.0000 0.1199
-4.750 -0.3965 0.03273 0.02816 -0.0135 1.0000 0.1310
-4.500 -0.4042 0.04441 0.03913 -0.0132 1.0000 0.1425
-4.250 -0.3861 0.04138 0.03603 -0.0128 1.0000 0.1582
-4.000 -0.3684 0.03866 0.03316 -0.0123 1.0000 0.1832
-3.750 -0.3511 0.03594 0.03042 -0.0113 1.0000 0.2111
-3.500 -0.2957 0.02978 0.02233 -0.0103 1.0000 0.0708
-3.250 -0.2698 0.02602 0.01800 -0.0088 1.0000 0.0589
-3.000 -0.2449 0.02364 0.01535 -0.0077 1.0000 0.0571
-2.750 -0.2219 0.02146 0.01305 -0.0069 1.0000 0.0627
-2.500 -0.1973 0.01968 0.01099 -0.0057 1.0000 0.0643
-2.250 -0.1737 0.01811 0.00926 -0.0043 1.0000 0.0673
-2.000 -0.1531 0.01677 0.00785 -0.0027 1.0000 0.0727
-1.750 -0.0212 0.01094 0.00518 -0.0186 1.0000 1.0000
-1.500 -0.0010 0.01088 0.00483 -0.0177 1.0000 1.0000
-1.250 0.0138 0.01093 0.00476 -0.0162 1.0000 1.0000
-1.000 0.0411 0.01114 0.00482 -0.0179 0.9842 1.0000
-0.750 0.1061 0.01113 0.00452 -0.0256 0.9470 1.0000
-0.500 0.1553 0.01111 0.00423 -0.0297 0.9054 1.0000
-0.250 0.1823 0.01123 0.00411 -0.0290 0.8663 1.0000
0.000 0.2027 0.01140 0.00407 -0.0271 0.8343 1.0000
0.250 0.2228 0.01160 0.00407 -0.0251 0.8068 1.0000
0.500 0.2433 0.01181 0.00411 -0.0234 0.7817 1.0000
0.750 0.2648 0.01203 0.00418 -0.0219 0.7591 1.0000
1.000 0.2864 0.01225 0.00425 -0.0204 0.7390 1.0000
1.250 0.3087 0.01249 0.00437 -0.0192 0.7189 1.0000
1.500 0.3312 0.01273 0.00450 -0.0180 0.7005 1.0000
1.750 0.3538 0.01298 0.00464 -0.0168 0.6838 1.0000
2.000 0.3771 0.01324 0.00485 -0.0159 0.6661 1.0000
2.250 0.4005 0.01351 0.00510 -0.0149 0.6494 1.0000
2.500 0.4239 0.01379 0.00532 -0.0140 0.6336 1.0000
2.750 0.4475 0.01407 0.00557 -0.0131 0.6184 1.0000
3.000 0.4713 0.01436 0.00583 -0.0121 0.6036 1.0000
3.250 0.4951 0.01466 0.00612 -0.0113 0.5890 1.0000
3.500 0.5192 0.01498 0.00651 -0.0105 0.5742 1.0000
3.750 0.5434 0.01530 0.00689 -0.0097 0.5590 1.0000
4.000 0.5677 0.01564 0.00730 -0.0090 0.5442 1.0000
4.250 0.5921 0.01600 0.00773 -0.0083 0.5297 1.0000
4.500 0.6166 0.01637 0.00820 -0.0076 0.5153 1.0000
4.750 0.6411 0.01675 0.00876 -0.0068 0.5005 1.0000
5.000 0.6656 0.01711 0.00925 -0.0061 0.4852 1.0000
5.250 0.6901 0.01745 0.00972 -0.0053 0.4696 1.0000
5.500 0.7146 0.01772 0.01009 -0.0043 0.4530 1.0000
5.750 0.7341 0.01667 0.00898 -0.0018 0.4004 1.0000
6.000 0.7529 0.01615 0.00837 0.0002 0.2960 1.0000
6.250 0.7596 0.01993 0.01045 0.0021 0.0607 1.0000
6.500 0.7778 0.02173 0.01245 0.0035 0.0500 1.0000
6.750 0.7938 0.02363 0.01442 0.0051 0.0450 1.0000
7.000 0.8119 0.02561 0.01643 0.0068 0.0420 1.0000
7.250 0.8331 0.02730 0.01822 0.0081 0.0380 1.0000
7.500 0.8549 0.02945 0.02046 0.0092 0.0359 1.0000
7.750 0.8782 0.03209 0.02330 0.0104 0.0359 1.0000
8.000 0.9003 0.03517 0.02678 0.0117 0.0370 1.0000
8.250 0.9184 0.03873 0.03086 0.0131 0.0388 1.0000
8.500 0.9326 0.04282 0.03541 0.0144 0.0409 1.0000
8.750 0.9435 0.04794 0.04084 0.0152 0.0430 1.0000
9.000 0.9491 0.05137 0.04516 0.0173 0.0489 1.0000
9.250 0.9502 0.05713 0.05125 0.0179 0.0536 1.0000
9.500 0.9533 0.06585 0.06029 0.0179 0.0676 1.0000
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Polar data table (+)
Polar graphs
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