EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 500,000 Max Cl/Cd: 75.94 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2070-il-500000-n5.txt Download as CSV file: xf-eh2070-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5468 0.08618 0.08414 0.0088 1.0000 0.0039
-7.750 -0.5501 0.08223 0.08023 0.0063 1.0000 0.0039
-7.500 -0.5534 0.07807 0.07608 0.0030 1.0000 0.0039
-7.250 -0.5503 0.07337 0.07137 -0.0005 1.0000 0.0040
-6.500 -0.5261 0.05769 0.05548 -0.0089 1.0000 0.0049
-6.250 -0.5144 0.05357 0.05122 -0.0104 1.0000 0.0052
-6.000 -0.4969 0.05307 0.05070 -0.0108 1.0000 0.0067
-5.750 -0.4798 0.04906 0.04656 -0.0117 1.0000 0.0075
-5.500 -0.4625 0.04454 0.04187 -0.0122 1.0000 0.0076
-5.250 -0.4451 0.03949 0.03660 -0.0121 1.0000 0.0068
-5.000 -0.4265 0.03382 0.03060 -0.0114 1.0000 0.0062
-4.750 -0.3964 0.02446 0.02052 -0.0118 0.9458 0.0056
-4.500 -0.3714 0.01959 0.01495 -0.0107 0.8900 0.0056
-4.250 -0.3503 0.01754 0.01239 -0.0089 0.8405 0.0060
-4.000 -0.3272 0.01623 0.01068 -0.0077 0.8022 0.0067
-3.750 -0.3025 0.01505 0.00914 -0.0067 0.7704 0.0075
-3.500 -0.2771 0.01422 0.00802 -0.0060 0.7426 0.0083
-3.250 -0.2509 0.01384 0.00744 -0.0056 0.7180 0.0092
-3.000 -0.2252 0.01271 0.00604 -0.0049 0.6967 0.0092
-2.750 -0.1997 0.01177 0.00484 -0.0042 0.6773 0.0092
-2.500 -0.1741 0.01104 0.00393 -0.0036 0.6594 0.0092
-2.250 -0.1483 0.01048 0.00322 -0.0030 0.6426 0.0092
-2.000 -0.1221 0.01006 0.00264 -0.0026 0.6259 0.0094
-1.750 -0.0956 0.00977 0.00221 -0.0022 0.6103 0.0097
-1.500 -0.0689 0.00947 0.00175 -0.0018 0.5953 0.0128
-1.250 -0.0421 0.00927 0.00151 -0.0015 0.5811 0.0292
-1.000 -0.0155 0.00906 0.00137 -0.0014 0.5675 0.0645
-0.750 0.0110 0.00882 0.00127 -0.0012 0.5546 0.1194
-0.500 0.0353 0.00813 0.00116 -0.0009 0.5422 0.3113
-0.250 0.0462 0.00632 0.00111 0.0023 0.5318 0.8353
0.000 0.0702 0.00624 0.00114 0.0036 0.5202 0.8939
0.250 0.0979 0.00628 0.00114 0.0041 0.5082 0.9300
0.500 0.1295 0.00636 0.00115 0.0035 0.4962 0.9518
0.750 0.1630 0.00645 0.00116 0.0024 0.4843 0.9673
1.000 0.2043 0.00658 0.00120 -0.0004 0.4717 0.9809
1.250 0.2428 0.00665 0.00120 -0.0028 0.4597 0.9847
1.500 0.2757 0.00671 0.00119 -0.0040 0.4484 0.9873
1.750 0.3075 0.00679 0.00120 -0.0049 0.4366 0.9901
2.000 0.3387 0.00687 0.00123 -0.0058 0.4245 0.9930
2.250 0.3707 0.00695 0.00126 -0.0068 0.4130 0.9953
2.500 0.4029 0.00703 0.00132 -0.0079 0.4019 0.9977
2.750 0.4351 0.00712 0.00137 -0.0090 0.3913 0.9999
3.000 0.4599 0.00720 0.00145 -0.0084 0.3821 1.0000
3.250 0.4845 0.00729 0.00153 -0.0078 0.3730 1.0000
3.500 0.5091 0.00741 0.00164 -0.0072 0.3629 1.0000
3.750 0.5338 0.00754 0.00179 -0.0067 0.3509 1.0000
4.250 0.5835 0.00782 0.00208 -0.0056 0.3268 1.0000
4.500 0.6083 0.00801 0.00225 -0.0051 0.3092 1.0000
4.750 0.6316 0.00847 0.00245 -0.0045 0.2490 1.0000
5.000 0.6536 0.00920 0.00281 -0.0039 0.1701 1.0000
5.250 0.6735 0.01038 0.00347 -0.0032 0.0638 1.0000
5.500 0.6952 0.01130 0.00421 -0.0024 0.0131 1.0000
5.750 0.7192 0.01180 0.00479 -0.0017 0.0082 1.0000
6.000 0.7433 0.01228 0.00538 -0.0011 0.0067 1.0000
6.250 0.7669 0.01290 0.00610 -0.0005 0.0055 1.0000
6.500 0.7892 0.01379 0.00713 0.0003 0.0048 1.0000
6.750 0.8092 0.01507 0.00859 0.0013 0.0044 1.0000
7.000 0.8307 0.01600 0.00962 0.0021 0.0039 1.0000
7.250 0.8542 0.01653 0.01022 0.0026 0.0034 1.0000
7.500 0.8753 0.01751 0.01138 0.0034 0.0031 1.0000
7.750 0.8954 0.01868 0.01267 0.0043 0.0029 1.0000
8.000 0.9153 0.01988 0.01402 0.0052 0.0026 1.0000
8.250 0.9354 0.02101 0.01527 0.0060 0.0023 1.0000
8.500 0.9542 0.02235 0.01676 0.0069 0.0021 1.0000
8.750 0.9722 0.02376 0.01832 0.0078 0.0019 1.0000
9.000 0.9882 0.02545 0.02019 0.0088 0.0018 1.0000
9.250 1.0002 0.02788 0.02288 0.0101 0.0017 1.0000
9.500 1.0067 0.03112 0.02646 0.0118 0.0016 1.0000
9.750 1.0081 0.03465 0.03035 0.0136 0.0016 1.0000
10.000 1.0033 0.03831 0.03435 0.0154 0.0016 1.0000
10.250 0.9935 0.04115 0.03741 0.0178 0.0016 1.0000
10.500 0.9810 0.04432 0.04078 0.0187 0.0016 1.0000
10.750 0.9714 0.04782 0.04446 0.0178 0.0016 1.0000
11.000 0.9521 0.05345 0.05029 0.0149 0.0016 1.0000
11.250 0.9521 0.05662 0.05357 0.0128 0.0016 1.0000
11.500 0.9317 0.06373 0.06086 0.0081 0.0016 1.0000
11.750 0.9188 0.07001 0.06728 0.0038 0.0016 1.0000
12.000 0.9041 0.07716 0.07455 -0.0010 0.0016 1.0000
12.250 0.8970 0.08309 0.08057 -0.0049 0.0016 1.0000
12.500 0.8855 0.09041 0.08798 -0.0096 0.0017 1.0000
12.750 0.8690 0.09957 0.09724 -0.0151 0.0017 1.0000
13.000 0.8546 0.10905 0.10679 -0.0202 0.0017 1.0000
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Polar data table (+)
Polar graphs
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