EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 50,000 Max Cl/Cd: 30.81 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2010-il-50000-n5.txt Download as CSV file: xf-eh2010-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5249 0.09784 0.09129 -0.0062 1.0000 0.0512
-9.000 -0.5264 0.09308 0.08660 -0.0089 1.0000 0.0508
-8.750 -0.5285 0.08832 0.08190 -0.0119 1.0000 0.0500
-8.500 -0.5348 0.08322 0.07686 -0.0154 1.0000 0.0494
-8.250 -0.5428 0.07868 0.07235 -0.0174 1.0000 0.0486
-8.000 -0.5496 0.07400 0.06765 -0.0190 1.0000 0.0480
-7.750 -0.5541 0.06935 0.06293 -0.0202 1.0000 0.0474
-7.500 -0.5568 0.06470 0.05815 -0.0208 1.0000 0.0469
-7.250 -0.5570 0.06012 0.05337 -0.0209 1.0000 0.0466
-7.000 -0.5543 0.05571 0.04870 -0.0206 1.0000 0.0465
-6.750 -0.5485 0.05156 0.04424 -0.0198 1.0000 0.0467
-6.500 -0.5398 0.04770 0.04002 -0.0188 1.0000 0.0474
-6.250 -0.5287 0.04426 0.03615 -0.0176 1.0000 0.0497
-6.000 -0.5159 0.04079 0.03201 -0.0160 1.0000 0.0525
-5.750 -0.5003 0.03759 0.02831 -0.0145 1.0000 0.0544
-5.500 -0.4821 0.03508 0.02560 -0.0134 1.0000 0.0565
-5.250 -0.4623 0.03289 0.02315 -0.0121 1.0000 0.0594
-5.000 -0.4414 0.03097 0.02075 -0.0108 1.0000 0.0658
-4.750 -0.4204 0.02916 0.01887 -0.0097 1.0000 0.0707
-4.500 -0.3975 0.02745 0.01694 -0.0086 1.0000 0.0759
-4.250 -0.3752 0.02604 0.01542 -0.0075 1.0000 0.0838
-4.000 -0.3538 0.02497 0.01421 -0.0063 1.0000 0.0953
-3.750 -0.3326 0.02393 0.01310 -0.0051 1.0000 0.1063
-3.500 -0.3155 0.02319 0.01240 -0.0036 1.0000 0.1228
-3.250 -0.2729 0.02201 0.01128 -0.0070 0.9808 0.1539
-3.000 -0.2312 0.02078 0.01023 -0.0102 0.9592 0.2036
-2.750 -0.1973 0.01908 0.00930 -0.0123 0.9373 0.3257
-2.500 -0.1489 0.01784 0.01003 -0.0118 0.9271 0.8395
-2.250 -0.0508 0.01848 0.01006 -0.0217 0.9200 0.9491
-2.000 0.0594 0.01800 0.00897 -0.0371 0.9065 1.0000
-1.750 0.0957 0.01790 0.00856 -0.0391 0.8711 1.0000
-1.500 0.1225 0.01788 0.00822 -0.0390 0.8398 1.0000
-1.250 0.1451 0.01790 0.00798 -0.0381 0.8133 1.0000
-1.000 0.1659 0.01794 0.00781 -0.0368 0.7891 1.0000
-0.750 0.1865 0.01801 0.00766 -0.0355 0.7677 1.0000
-0.500 0.2070 0.01809 0.00753 -0.0342 0.7479 1.0000
-0.250 0.2276 0.01819 0.00745 -0.0328 0.7302 1.0000
0.000 0.2484 0.01831 0.00741 -0.0316 0.7129 1.0000
0.250 0.2694 0.01845 0.00742 -0.0304 0.6965 1.0000
0.500 0.2904 0.01860 0.00745 -0.0293 0.6810 1.0000
0.750 0.3117 0.01877 0.00750 -0.0281 0.6663 1.0000
1.000 0.3330 0.01895 0.00759 -0.0270 0.6522 1.0000
1.250 0.3544 0.01915 0.00772 -0.0259 0.6386 1.0000
1.500 0.3759 0.01937 0.00786 -0.0248 0.6255 1.0000
1.750 0.3975 0.01960 0.00802 -0.0237 0.6129 1.0000
2.000 0.4192 0.01983 0.00820 -0.0225 0.6009 1.0000
2.250 0.4408 0.02009 0.00841 -0.0214 0.5890 1.0000
2.500 0.4629 0.02038 0.00873 -0.0205 0.5766 1.0000
2.750 0.4850 0.02069 0.00904 -0.0196 0.5647 1.0000
3.000 0.5070 0.02102 0.00937 -0.0186 0.5532 1.0000
3.250 0.5290 0.02134 0.00969 -0.0176 0.5422 1.0000
3.500 0.5512 0.02164 0.01001 -0.0165 0.5321 1.0000
3.750 0.5729 0.02204 0.01047 -0.0155 0.5203 1.0000
4.000 0.5946 0.02246 0.01095 -0.0146 0.5092 1.0000
4.250 0.6165 0.02286 0.01140 -0.0136 0.4986 1.0000
4.500 0.6387 0.02323 0.01179 -0.0125 0.4887 1.0000
4.750 0.6603 0.02368 0.01238 -0.0115 0.4778 1.0000
5.000 0.6816 0.02418 0.01300 -0.0105 0.4667 1.0000
5.250 0.7032 0.02466 0.01359 -0.0095 0.4563 1.0000
5.500 0.7255 0.02508 0.01407 -0.0085 0.4465 1.0000
5.750 0.7469 0.02560 0.01478 -0.0075 0.4357 1.0000
6.000 0.7678 0.02620 0.01554 -0.0065 0.4244 1.0000
6.250 0.7890 0.02677 0.01627 -0.0055 0.4137 1.0000
6.500 0.8109 0.02726 0.01688 -0.0044 0.4034 1.0000
6.750 0.8327 0.02776 0.01753 -0.0034 0.3927 1.0000
7.000 0.8527 0.02844 0.01843 -0.0024 0.3807 1.0000
7.250 0.8728 0.02911 0.01937 -0.0013 0.3689 1.0000
7.500 0.8929 0.02974 0.02022 -0.0002 0.3569 1.0000
7.750 0.9130 0.03034 0.02102 0.0010 0.3445 1.0000
8.000 0.9327 0.03091 0.02181 0.0022 0.3315 1.0000
8.250 0.9514 0.03148 0.02260 0.0035 0.3171 1.0000
8.500 0.9689 0.03194 0.02328 0.0050 0.3005 1.0000
8.750 0.9855 0.03199 0.02350 0.0069 0.2800 1.0000
9.000 0.9938 0.03229 0.02393 0.0090 0.2500 1.0000
9.250 0.9986 0.03300 0.02468 0.0112 0.2155 1.0000
9.500 1.0012 0.03428 0.02596 0.0132 0.1818 1.0000
9.750 0.9977 0.03621 0.02776 0.0152 0.1473 1.0000
10.000 0.9866 0.03875 0.03009 0.0174 0.1200 1.0000
10.250 0.9742 0.04182 0.03302 0.0187 0.1017 1.0000
10.500 0.9623 0.04541 0.03651 0.0188 0.0890 1.0000
10.750 0.9511 0.04932 0.04031 0.0183 0.0800 1.0000
11.000 0.9426 0.05325 0.04427 0.0176 0.0710 1.0000
11.250 0.9352 0.05714 0.04814 0.0168 0.0650 1.0000
11.500 0.9296 0.06094 0.05198 0.0161 0.0595 1.0000
11.750 0.9244 0.06467 0.05563 0.0154 0.0560 1.0000
12.000 0.9224 0.06831 0.05948 0.0149 0.0512 1.0000
12.250 0.9191 0.07207 0.06328 0.0139 0.0475 1.0000
12.500 0.9172 0.07553 0.06669 0.0133 0.0449 1.0000
12.750 0.9164 0.07942 0.07084 0.0126 0.0423 1.0000
13.000 0.9159 0.08331 0.07496 0.0119 0.0407 1.0000
13.250 0.9135 0.08765 0.07950 0.0108 0.0393 1.0000
13.500 0.9092 0.09239 0.08443 0.0091 0.0383 1.0000
13.750 0.9031 0.09759 0.08981 0.0070 0.0376 1.0000
14.000 0.8949 0.10340 0.09578 0.0043 0.0368 1.0000
14.250 0.8854 0.10966 0.10218 0.0012 0.0362 1.0000
14.500 0.8678 0.11854 0.11129 -0.0036 0.0368 1.0000
14.750 0.8418 0.13051 0.12343 -0.0103 0.0384 1.0000
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Polar data table (+)
Polar graphs
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