EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 500,000 Max Cl/Cd: 68.85 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1090-il-500000-n5.txt Download as CSV file: xf-eh1090-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.0/9.0
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.8159 0.04508 0.04257 -0.0214 1.0000 0.0049
-9.500 -0.8345 0.03911 0.03619 -0.0197 1.0000 0.0049
-9.250 -0.8395 0.03452 0.03117 -0.0179 1.0000 0.0050
-9.000 -0.8339 0.03119 0.02745 -0.0162 1.0000 0.0051
-8.750 -0.8236 0.02841 0.02429 -0.0147 1.0000 0.0052
-8.500 -0.8163 0.02471 0.02010 -0.0127 1.0000 0.0054
-8.250 -0.8003 0.02261 0.01771 -0.0114 1.0000 0.0056
-8.000 -0.7808 0.02125 0.01613 -0.0105 1.0000 0.0058
-7.750 -0.7602 0.02001 0.01471 -0.0096 1.0000 0.0060
-7.500 -0.7381 0.01913 0.01372 -0.0088 1.0000 0.0063
-7.250 -0.7155 0.01835 0.01283 -0.0082 1.0000 0.0067
-7.000 -0.6929 0.01747 0.01182 -0.0074 1.0000 0.0071
-6.750 -0.6707 0.01650 0.01070 -0.0064 1.0000 0.0074
-6.500 -0.6488 0.01547 0.00952 -0.0054 1.0000 0.0076
-6.250 -0.6266 0.01460 0.00854 -0.0044 1.0000 0.0078
-6.000 -0.6043 0.01386 0.00767 -0.0033 1.0000 0.0082
-5.750 -0.5819 0.01325 0.00697 -0.0023 1.0000 0.0085
-5.500 -0.5604 0.01251 0.00615 -0.0011 0.9999 0.0089
-5.250 -0.5277 0.01177 0.00533 -0.0023 0.9915 0.0100
-5.000 -0.4940 0.01130 0.00481 -0.0038 0.9817 0.0111
-4.750 -0.4606 0.01089 0.00435 -0.0050 0.9686 0.0126
-4.500 -0.4277 0.01049 0.00387 -0.0061 0.9517 0.0157
-4.250 -0.3961 0.01012 0.00349 -0.0069 0.9303 0.0220
-4.000 -0.3687 0.00981 0.00316 -0.0067 0.9052 0.0336
-3.750 -0.3436 0.00957 0.00290 -0.0060 0.8790 0.0470
-3.500 -0.3189 0.00934 0.00266 -0.0053 0.8534 0.0667
-3.250 -0.2943 0.00910 0.00243 -0.0046 0.8285 0.0951
-3.000 -0.2693 0.00886 0.00223 -0.0040 0.8044 0.1261
-2.750 -0.2440 0.00864 0.00204 -0.0035 0.7812 0.1614
-2.500 -0.2188 0.00839 0.00186 -0.0030 0.7590 0.2069
-2.250 -0.1937 0.00810 0.00170 -0.0025 0.7373 0.2660
-2.000 -0.1685 0.00781 0.00153 -0.0021 0.7169 0.3310
-1.750 -0.1438 0.00748 0.00139 -0.0016 0.6967 0.4115
-1.500 -0.1205 0.00700 0.00127 -0.0009 0.6777 0.5288
-1.250 -0.0961 0.00672 0.00120 -0.0002 0.6591 0.6097
-1.000 -0.0710 0.00654 0.00115 0.0005 0.6410 0.6701
-0.750 -0.0452 0.00647 0.00112 0.0010 0.6234 0.7103
-0.500 -0.0195 0.00639 0.00111 0.0016 0.6063 0.7520
-0.250 0.0059 0.00634 0.00112 0.0023 0.5896 0.7937
0.000 0.0317 0.00633 0.00114 0.0030 0.5729 0.8265
0.250 0.0578 0.00635 0.00116 0.0035 0.5565 0.8518
0.500 0.0838 0.00638 0.00120 0.0042 0.5408 0.8758
0.750 0.1099 0.00644 0.00124 0.0048 0.5257 0.8980
1.000 0.1367 0.00651 0.00129 0.0052 0.5107 0.9154
1.250 0.1644 0.00660 0.00134 0.0054 0.4959 0.9289
1.500 0.1931 0.00670 0.00139 0.0054 0.4804 0.9393
1.750 0.2232 0.00680 0.00144 0.0049 0.4645 0.9465
2.000 0.2525 0.00690 0.00150 0.0047 0.4491 0.9543
2.250 0.2846 0.00702 0.00156 0.0038 0.4331 0.9597
2.500 0.3154 0.00714 0.00163 0.0031 0.4174 0.9662
2.750 0.3471 0.00727 0.00173 0.0023 0.4014 0.9712
3.000 0.3799 0.00742 0.00182 0.0011 0.3823 0.9751
3.250 0.4112 0.00760 0.00191 0.0003 0.3590 0.9797
3.500 0.4433 0.00775 0.00203 -0.0008 0.3407 0.9834
3.750 0.4773 0.00790 0.00216 -0.0022 0.3245 0.9860
4.000 0.5103 0.00806 0.00230 -0.0035 0.3089 0.9893
4.250 0.5421 0.00828 0.00246 -0.0045 0.2870 0.9927
4.500 0.5743 0.00851 0.00263 -0.0056 0.2626 0.9956
4.750 0.6066 0.00881 0.00285 -0.0069 0.2314 0.9984
5.000 0.6326 0.00945 0.00315 -0.0071 0.1639 1.0000
5.250 0.6530 0.01003 0.00349 -0.0060 0.1145 1.0000
5.500 0.6744 0.01051 0.00384 -0.0050 0.0839 1.0000
5.750 0.6955 0.01106 0.00424 -0.0040 0.0527 1.0000
6.000 0.7165 0.01165 0.00471 -0.0029 0.0277 1.0000
6.250 0.7384 0.01213 0.00519 -0.0020 0.0173 1.0000
6.500 0.7605 0.01262 0.00569 -0.0010 0.0131 1.0000
6.750 0.7829 0.01308 0.00621 -0.0001 0.0108 1.0000
7.000 0.8055 0.01353 0.00674 0.0008 0.0099 1.0000
7.250 0.8279 0.01404 0.00732 0.0016 0.0091 1.0000
7.500 0.8499 0.01463 0.00798 0.0025 0.0083 1.0000
7.750 0.8701 0.01548 0.00895 0.0035 0.0074 1.0000
8.000 0.8909 0.01623 0.00980 0.0045 0.0068 1.0000
8.250 0.9134 0.01674 0.01038 0.0052 0.0062 1.0000
8.500 0.9340 0.01749 0.01122 0.0061 0.0058 1.0000
8.750 0.9540 0.01831 0.01214 0.0070 0.0054 1.0000
9.000 0.9738 0.01912 0.01303 0.0080 0.0051 1.0000
9.250 0.9925 0.02003 0.01403 0.0090 0.0048 1.0000
9.500 1.0098 0.02107 0.01517 0.0101 0.0046 1.0000
9.750 1.0221 0.02267 0.01692 0.0118 0.0043 1.0000
10.000 1.0338 0.02430 0.01875 0.0135 0.0041 1.0000
10.250 1.0475 0.02560 0.02020 0.0149 0.0040 1.0000
10.500 1.0591 0.02702 0.02180 0.0164 0.0039 1.0000
10.750 1.0679 0.02862 0.02358 0.0182 0.0037 1.0000
11.000 1.0708 0.03036 0.02551 0.0207 0.0037 1.0000
11.250 1.0693 0.03226 0.02759 0.0233 0.0037 1.0000
11.500 1.0649 0.03458 0.03011 0.0253 0.0036 1.0000
11.750 1.0609 0.03705 0.03277 0.0263 0.0035 1.0000
12.000 1.0542 0.04015 0.03606 0.0265 0.0035 1.0000
12.250 1.0439 0.04406 0.04018 0.0257 0.0034 1.0000
12.500 1.0339 0.04835 0.04466 0.0240 0.0034 1.0000
12.750 1.0238 0.05303 0.04950 0.0216 0.0035 1.0000
13.000 1.0060 0.05938 0.05607 0.0180 0.0034 1.0000
13.250 0.9943 0.06508 0.06192 0.0145 0.0035 1.0000
13.500 0.9775 0.07208 0.06907 0.0101 0.0035 1.0000
13.750 0.9585 0.07993 0.07708 0.0052 0.0034 1.0000
14.000 0.9411 0.08783 0.08510 0.0003 0.0035 1.0000
14.250 0.9220 0.09660 0.09399 -0.0050 0.0036 1.0000
14.500 0.9009 0.10651 0.10402 -0.0108 0.0035 1.0000
14.750 0.8793 0.11710 0.11471 -0.0166 0.0037 1.0000
15.000 0.8479 0.13126 0.12897 -0.0239 0.0038 1.0000
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Polar data table (+)
Polar graphs
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