EH 1.5/9.0 (eh1590-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.5/9.0 (eh1590-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.12 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1590-il-1000000-n5.txt Download as CSV file: xf-eh1590-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.5/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.8571 0.03747 0.03536 -0.0183 1.0000 0.0035
-9.500 -0.8655 0.03109 0.02848 -0.0163 1.0000 0.0036
-9.250 -0.8592 0.02744 0.02445 -0.0146 1.0000 0.0037
-9.000 -0.8460 0.02497 0.02169 -0.0132 1.0000 0.0038
-8.750 -0.8312 0.02264 0.01905 -0.0119 1.0000 0.0039
-8.500 -0.8133 0.02083 0.01698 -0.0107 1.0000 0.0040
-8.250 -0.7937 0.01931 0.01524 -0.0097 1.0000 0.0041
-8.000 -0.7731 0.01795 0.01365 -0.0087 1.0000 0.0042
-7.750 -0.7514 0.01682 0.01234 -0.0078 1.0000 0.0043
-7.500 -0.7284 0.01596 0.01135 -0.0071 1.0000 0.0044
-7.250 -0.7048 0.01528 0.01057 -0.0065 1.0000 0.0045
-7.000 -0.6811 0.01460 0.00978 -0.0058 1.0000 0.0046
-6.750 -0.6525 0.01386 0.00893 -0.0061 0.9898 0.0047
-6.500 -0.6178 0.01303 0.00798 -0.0079 0.9685 0.0047
-6.250 -0.5887 0.01177 0.00647 -0.0083 0.9331 0.0051
-6.000 -0.5661 0.01121 0.00571 -0.0071 0.8927 0.0055
-5.750 -0.5426 0.01090 0.00523 -0.0061 0.8578 0.0058
-5.500 -0.5181 0.01061 0.00480 -0.0054 0.8275 0.0061
-5.250 -0.4930 0.01036 0.00441 -0.0048 0.7990 0.0065
-5.000 -0.4674 0.01011 0.00403 -0.0043 0.7737 0.0068
-4.750 -0.4415 0.00989 0.00368 -0.0038 0.7497 0.0072
-4.500 -0.4153 0.00967 0.00334 -0.0035 0.7281 0.0076
-4.250 -0.3889 0.00949 0.00305 -0.0031 0.7072 0.0078
-4.000 -0.3625 0.00925 0.00270 -0.0028 0.6884 0.0090
-3.750 -0.3360 0.00905 0.00246 -0.0025 0.6699 0.0112
-3.500 -0.3093 0.00888 0.00223 -0.0022 0.6523 0.0156
-3.250 -0.2825 0.00872 0.00203 -0.0020 0.6357 0.0222
-3.000 -0.2556 0.00857 0.00185 -0.0018 0.6201 0.0314
-2.750 -0.2286 0.00843 0.00170 -0.0016 0.6054 0.0425
-2.500 -0.2017 0.00829 0.00156 -0.0015 0.5905 0.0561
-2.250 -0.1747 0.00814 0.00144 -0.0013 0.5765 0.0763
-2.000 -0.1479 0.00797 0.00131 -0.0011 0.5628 0.1053
-1.750 -0.1209 0.00783 0.00122 -0.0010 0.5497 0.1315
-1.500 -0.0941 0.00767 0.00112 -0.0009 0.5368 0.1676
-1.000 -0.0408 0.00726 0.00095 -0.0005 0.5119 0.2733
-0.750 -0.0149 0.00696 0.00087 -0.0003 0.5004 0.3567
-0.500 0.0099 0.00652 0.00079 0.0001 0.4890 0.4810
-0.250 0.0346 0.00612 0.00073 0.0006 0.4780 0.5975
0.000 0.0597 0.00587 0.00071 0.0011 0.4669 0.6825
0.250 0.0855 0.00573 0.00071 0.0016 0.4558 0.7408
0.500 0.1117 0.00565 0.00073 0.0020 0.4449 0.7848
0.750 0.1374 0.00558 0.00077 0.0026 0.4345 0.8290
1.500 0.2145 0.00559 0.00094 0.0046 0.4029 0.9180
1.750 0.2419 0.00566 0.00098 0.0047 0.3927 0.9262
2.000 0.2695 0.00573 0.00103 0.0048 0.3821 0.9333
2.250 0.2970 0.00582 0.00108 0.0050 0.3710 0.9409
2.500 0.3253 0.00590 0.00113 0.0049 0.3603 0.9470
2.750 0.3531 0.00599 0.00120 0.0050 0.3500 0.9539
3.000 0.3824 0.00609 0.00128 0.0046 0.3388 0.9590
3.250 0.4117 0.00621 0.00136 0.0043 0.3278 0.9645
3.500 0.4406 0.00633 0.00144 0.0041 0.3161 0.9697
3.750 0.4720 0.00646 0.00154 0.0032 0.3033 0.9730
4.000 0.5027 0.00660 0.00166 0.0025 0.2900 0.9768
4.250 0.5318 0.00675 0.00177 0.0022 0.2763 0.9812
4.500 0.5632 0.00692 0.00190 0.0013 0.2610 0.9837
4.750 0.5949 0.00718 0.00206 0.0002 0.2341 0.9857
5.000 0.6259 0.00753 0.00228 -0.0008 0.1991 0.9879
5.250 0.6553 0.00808 0.00258 -0.0016 0.1456 0.9907
5.500 0.6842 0.00855 0.00288 -0.0022 0.1094 0.9934
5.750 0.7142 0.00909 0.00324 -0.0032 0.0724 0.9956
6.000 0.7438 0.00975 0.00370 -0.0041 0.0332 0.9979
6.250 0.7738 0.01028 0.00415 -0.0049 0.0146 0.9999
6.500 0.7971 0.01059 0.00446 -0.0042 0.0109 1.0000
6.750 0.8195 0.01095 0.00482 -0.0033 0.0086 1.0000
7.000 0.8424 0.01128 0.00519 -0.0024 0.0074 1.0000
7.250 0.8655 0.01158 0.00553 -0.0017 0.0067 1.0000
7.500 0.8885 0.01193 0.00591 -0.0009 0.0060 1.0000
7.750 0.9112 0.01234 0.00636 -0.0002 0.0054 1.0000
8.000 0.9327 0.01295 0.00706 0.0008 0.0046 1.0000
8.250 0.9559 0.01335 0.00749 0.0015 0.0044 1.0000
8.500 0.9789 0.01377 0.00797 0.0021 0.0042 1.0000
8.750 1.0015 0.01426 0.00851 0.0028 0.0038 1.0000
9.000 1.0236 0.01480 0.00912 0.0035 0.0036 1.0000
9.250 1.0455 0.01535 0.00973 0.0042 0.0033 1.0000
9.500 1.0674 0.01589 0.01033 0.0048 0.0030 1.0000
9.750 1.0886 0.01648 0.01097 0.0056 0.0028 1.0000
10.000 1.1054 0.01756 0.01217 0.0068 0.0025 1.0000
10.250 1.1241 0.01835 0.01305 0.0078 0.0024 1.0000
10.500 1.1426 0.01912 0.01391 0.0088 0.0023 1.0000
10.750 1.1601 0.01995 0.01483 0.0099 0.0022 1.0000
11.000 1.1762 0.02084 0.01581 0.0111 0.0022 1.0000
11.250 1.1906 0.02181 0.01689 0.0125 0.0022 1.0000
11.500 1.2019 0.02295 0.01814 0.0142 0.0021 1.0000
11.750 1.2111 0.02409 0.01939 0.0161 0.0020 1.0000
12.000 1.2131 0.02528 0.02072 0.0190 0.0020 1.0000
12.250 1.2133 0.02668 0.02223 0.0216 0.0020 1.0000
12.500 1.2096 0.02863 0.02432 0.0235 0.0020 1.0000
12.750 1.2099 0.03060 0.02641 0.0244 0.0019 1.0000
13.000 1.2064 0.03325 0.02919 0.0246 0.0019 1.0000
13.250 1.2065 0.03583 0.03190 0.0243 0.0019 1.0000
13.500 1.1973 0.03978 0.03600 0.0232 0.0019 1.0000
13.750 1.1970 0.04286 0.03920 0.0221 0.0018 1.0000
14.000 1.1961 0.04617 0.04260 0.0206 0.0018 1.0000
14.250 1.1897 0.05036 0.04691 0.0188 0.0018 1.0000
14.500 1.1790 0.05527 0.05196 0.0165 0.0017 1.0000
14.750 1.1615 0.06135 0.05820 0.0136 0.0018 1.0000
15.000 1.1582 0.06549 0.06242 0.0114 0.0017 1.0000
15.250 1.1401 0.07202 0.06910 0.0081 0.0017 1.0000
15.500 1.1243 0.07858 0.07578 0.0047 0.0017 1.0000
15.750 1.1115 0.08490 0.08221 0.0013 0.0017 1.0000
16.000 1.0983 0.09158 0.08900 -0.0024 0.0017 1.0000
16.250 1.0776 0.09990 0.09746 -0.0069 0.0017 1.0000
16.500 1.0518 0.10972 0.10743 -0.0122 0.0018 1.0000
16.750 1.0385 0.11722 0.11502 -0.0163 0.0017 1.0000
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Polar data table (+)
Polar graphs
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