EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 500,000 Max Cl/Cd: 54.98 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh0009-il-500000-n5.txt Download as CSV file: xf-eh0009-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8680 0.08047 0.07816 -0.0028 1.0000 0.0029
-12.500 -0.8940 0.06909 0.06665 -0.0104 1.0000 0.0028
-12.250 -0.9198 0.05876 0.05614 -0.0184 1.0000 0.0027
-12.000 -0.9403 0.05129 0.04847 -0.0241 1.0000 0.0027
-11.750 -0.9611 0.04543 0.04240 -0.0274 1.0000 0.0027
-11.500 -0.9805 0.04096 0.03770 -0.0280 1.0000 0.0026
-11.250 -0.9944 0.03782 0.03434 -0.0265 1.0000 0.0026
-11.000 -1.0040 0.03540 0.03171 -0.0237 1.0000 0.0028
-10.750 -1.0096 0.03274 0.02878 -0.0209 1.0000 0.0028
-10.500 -1.0073 0.03025 0.02601 -0.0188 1.0000 0.0028
-10.250 -1.0001 0.02807 0.02355 -0.0170 1.0000 0.0029
-10.000 -0.9883 0.02626 0.02149 -0.0154 1.0000 0.0032
-9.750 -0.9753 0.02446 0.01945 -0.0139 1.0000 0.0033
-9.500 -0.9595 0.02297 0.01775 -0.0126 1.0000 0.0035
-9.250 -0.9424 0.02162 0.01619 -0.0114 1.0000 0.0036
-9.000 -0.9223 0.02071 0.01513 -0.0104 1.0000 0.0038
-8.750 -0.9061 0.01913 0.01336 -0.0090 1.0000 0.0041
-8.500 -0.8871 0.01800 0.01207 -0.0079 1.0000 0.0044
-8.250 -0.8654 0.01728 0.01127 -0.0071 1.0000 0.0048
-8.000 -0.8435 0.01659 0.01049 -0.0063 1.0000 0.0052
-7.750 -0.8208 0.01600 0.00984 -0.0056 1.0000 0.0059
-7.500 -0.7976 0.01552 0.00928 -0.0050 1.0000 0.0065
-7.250 -0.7761 0.01476 0.00843 -0.0040 1.0000 0.0073
-7.000 -0.7544 0.01406 0.00767 -0.0031 1.0000 0.0084
-6.750 -0.7316 0.01353 0.00709 -0.0022 1.0000 0.0093
-6.500 -0.7087 0.01306 0.00652 -0.0014 1.0000 0.0104
-6.250 -0.6853 0.01273 0.00614 -0.0006 1.0000 0.0116
-6.000 -0.6639 0.01207 0.00543 0.0005 1.0000 0.0145
-5.750 -0.6412 0.01167 0.00499 0.0015 1.0000 0.0171
-5.500 -0.6182 0.01133 0.00460 0.0024 1.0000 0.0199
-5.250 -0.5959 0.01094 0.00421 0.0034 1.0000 0.0258
-5.000 -0.5718 0.01056 0.00387 0.0040 0.9993 0.0367
-4.750 -0.5391 0.01009 0.00350 0.0026 0.9951 0.0599
-4.500 -0.5074 0.00965 0.00319 0.0015 0.9904 0.0900
-4.250 -0.4748 0.00926 0.00291 0.0002 0.9854 0.1200
-4.000 -0.4418 0.00884 0.00265 -0.0012 0.9801 0.1607
-3.750 -0.4103 0.00848 0.00243 -0.0022 0.9722 0.1994
-3.500 -0.3785 0.00811 0.00221 -0.0033 0.9639 0.2441
-3.250 -0.3465 0.00777 0.00203 -0.0044 0.9547 0.2928
-3.000 -0.3162 0.00749 0.00188 -0.0050 0.9426 0.3313
-2.750 -0.2872 0.00723 0.00174 -0.0053 0.9287 0.3723
-2.500 -0.2596 0.00702 0.00160 -0.0052 0.9136 0.4084
-2.250 -0.2332 0.00685 0.00149 -0.0048 0.8972 0.4422
-2.000 -0.2073 0.00668 0.00140 -0.0043 0.8793 0.4769
-1.750 -0.1815 0.00656 0.00132 -0.0037 0.8603 0.5093
-1.500 -0.1557 0.00645 0.00124 -0.0032 0.8409 0.5391
-1.250 -0.1298 0.00636 0.00117 -0.0026 0.8208 0.5685
-1.000 -0.1040 0.00628 0.00112 -0.0021 0.8007 0.5991
-0.750 -0.0781 0.00621 0.00109 -0.0015 0.7790 0.6290
-0.500 -0.0521 0.00617 0.00106 -0.0010 0.7562 0.6565
-0.250 -0.0261 0.00616 0.00104 -0.0005 0.7323 0.6823
0.000 0.0000 0.00615 0.00103 0.0000 0.7075 0.7074
0.250 0.0260 0.00616 0.00104 0.0005 0.6823 0.7323
0.500 0.0520 0.00617 0.00106 0.0010 0.6565 0.7562
0.750 0.0780 0.00621 0.00109 0.0016 0.6291 0.7789
1.000 0.1039 0.00628 0.00112 0.0021 0.5993 0.8007
1.250 0.1297 0.00636 0.00117 0.0026 0.5684 0.8208
1.500 0.1556 0.00645 0.00124 0.0032 0.5390 0.8410
1.750 0.1815 0.00656 0.00132 0.0037 0.5094 0.8604
2.000 0.2072 0.00668 0.00140 0.0043 0.4772 0.8793
2.250 0.2331 0.00685 0.00149 0.0048 0.4422 0.8971
2.500 0.2596 0.00702 0.00160 0.0052 0.4084 0.9137
2.750 0.2871 0.00723 0.00174 0.0053 0.3723 0.9288
3.000 0.3162 0.00749 0.00188 0.0050 0.3316 0.9426
3.250 0.3465 0.00777 0.00203 0.0044 0.2921 0.9548
3.500 0.3786 0.00810 0.00221 0.0033 0.2462 0.9640
3.750 0.4104 0.00848 0.00243 0.0022 0.2002 0.9723
4.000 0.4419 0.00885 0.00266 0.0012 0.1598 0.9803
4.250 0.4750 0.00926 0.00291 -0.0002 0.1199 0.9855
4.500 0.5076 0.00965 0.00319 -0.0015 0.0900 0.9906
4.750 0.5394 0.01009 0.00350 -0.0027 0.0601 0.9953
5.000 0.5720 0.01056 0.00387 -0.0040 0.0367 0.9995
5.250 0.5956 0.01094 0.00421 -0.0033 0.0258 1.0000
5.500 0.6179 0.01133 0.00460 -0.0023 0.0199 1.0000
5.750 0.6409 0.01166 0.00498 -0.0014 0.0172 1.0000
6.000 0.6636 0.01207 0.00542 -0.0005 0.0145 1.0000
6.250 0.6850 0.01273 0.00614 0.0007 0.0116 1.0000
6.500 0.7085 0.01307 0.00653 0.0014 0.0104 1.0000
6.750 0.7315 0.01353 0.00709 0.0023 0.0093 1.0000
7.000 0.7543 0.01406 0.00767 0.0031 0.0084 1.0000
7.250 0.7761 0.01477 0.00844 0.0040 0.0073 1.0000
7.500 0.7979 0.01550 0.00925 0.0049 0.0065 1.0000
7.750 0.8211 0.01599 0.00982 0.0056 0.0058 1.0000
8.000 0.8434 0.01663 0.01054 0.0063 0.0053 1.0000
8.250 0.8654 0.01732 0.01131 0.0071 0.0048 1.0000
8.500 0.8872 0.01804 0.01211 0.0079 0.0045 1.0000
8.750 0.9065 0.01912 0.01335 0.0089 0.0041 1.0000
9.000 0.9231 0.02064 0.01505 0.0103 0.0038 1.0000
9.250 0.9423 0.02172 0.01630 0.0113 0.0037 1.0000
9.500 0.9597 0.02302 0.01780 0.0125 0.0035 1.0000
9.750 0.9757 0.02448 0.01947 0.0138 0.0033 1.0000
10.000 0.9893 0.02619 0.02142 0.0153 0.0031 1.0000
10.250 1.0004 0.02811 0.02359 0.0169 0.0030 1.0000
10.500 1.0081 0.03025 0.02601 0.0187 0.0028 1.0000
10.750 1.0100 0.03280 0.02884 0.0208 0.0028 1.0000
11.000 1.0057 0.03535 0.03166 0.0235 0.0027 1.0000
11.250 0.9931 0.03807 0.03461 0.0265 0.0027 1.0000
11.500 0.9800 0.04115 0.03790 0.0278 0.0027 1.0000
11.750 0.9603 0.04569 0.04267 0.0271 0.0027 1.0000
12.000 0.9422 0.05119 0.04837 0.0240 0.0027 1.0000
12.250 0.9204 0.05892 0.05630 0.0181 0.0027 1.0000
12.500 0.8972 0.06869 0.06624 0.0105 0.0028 1.0000
12.750 0.8677 0.08098 0.07867 0.0022 0.0029 1.0000
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Polar data table (+)
Polar graphs
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