EH 2.5/10 (eh2510-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.5/10 (eh2510-il) Reynolds number: 50,000 Max Cl/Cd: 30.87 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2510-il-50000-n5.txt Download as CSV file: xf-eh2510-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.5/10
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5080 0.08974 0.08341 -0.0161 1.0000 0.0548
-8.250 -0.4998 0.08593 0.07964 -0.0154 1.0000 0.0536
-8.000 -0.5007 0.08201 0.07576 -0.0162 1.0000 0.0526
-7.750 -0.5012 0.07793 0.07168 -0.0174 1.0000 0.0517
-7.500 -0.5015 0.07378 0.06750 -0.0185 1.0000 0.0507
-7.250 -0.5009 0.06956 0.06322 -0.0194 1.0000 0.0499
-7.000 -0.4986 0.06536 0.05892 -0.0200 1.0000 0.0490
-6.750 -0.4946 0.06115 0.05456 -0.0202 1.0000 0.0483
-6.500 -0.4885 0.05704 0.05025 -0.0200 1.0000 0.0478
-6.250 -0.4804 0.05308 0.04603 -0.0195 1.0000 0.0474
-6.000 -0.4704 0.04931 0.04195 -0.0187 1.0000 0.0472
-5.750 -0.4582 0.04618 0.03852 -0.0177 1.0000 0.0489
-5.500 -0.4448 0.04319 0.03515 -0.0165 1.0000 0.0515
-5.250 -0.4304 0.04023 0.03170 -0.0149 1.0000 0.0537
-5.000 -0.4148 0.03750 0.02850 -0.0132 1.0000 0.0546
-4.750 -0.3988 0.03503 0.02563 -0.0114 1.0000 0.0551
-4.500 -0.3838 0.03278 0.02318 -0.0097 1.0000 0.0559
-4.250 -0.3660 0.03091 0.02115 -0.0086 0.9959 0.0573
-4.000 -0.3225 0.02862 0.01851 -0.0118 0.9710 0.0601
-3.750 -0.2764 0.02654 0.01603 -0.0149 0.9491 0.0648
-3.500 -0.2301 0.02488 0.01417 -0.0179 0.9271 0.0736
-3.250 -0.1854 0.02370 0.01284 -0.0208 0.9045 0.0931
-3.000 -0.1453 0.02254 0.01157 -0.0228 0.8816 0.1244
-2.750 -0.1137 0.02151 0.01062 -0.0234 0.8578 0.1663
-2.500 -0.0888 0.02050 0.00977 -0.0226 0.8358 0.2150
-2.250 -0.0538 0.01781 0.00977 -0.0215 0.8186 0.8024
-2.000 0.0937 0.01829 0.00922 -0.0399 0.7992 0.9953
-1.750 0.1221 0.01827 0.00880 -0.0401 0.7770 1.0000
1.750 0.4204 0.02033 0.00855 -0.0246 0.5835 1.0000
2.000 0.4421 0.02057 0.00873 -0.0236 0.5710 1.0000
2.250 0.4636 0.02081 0.00892 -0.0225 0.5588 1.0000
2.500 0.4851 0.02104 0.00910 -0.0214 0.5467 1.0000
2.750 0.5064 0.02126 0.00927 -0.0202 0.5342 1.0000
3.000 0.5279 0.02149 0.00944 -0.0190 0.5230 1.0000
3.250 0.5495 0.02172 0.00969 -0.0178 0.5117 1.0000
3.500 0.5710 0.02206 0.01007 -0.0168 0.5006 1.0000
3.750 0.5928 0.02241 0.01044 -0.0159 0.4908 1.0000
4.000 0.6152 0.02270 0.01071 -0.0149 0.4829 1.0000
4.250 0.6368 0.02319 0.01131 -0.0141 0.4735 1.0000
4.500 0.6589 0.02360 0.01176 -0.0132 0.4656 1.0000
4.750 0.6807 0.02404 0.01236 -0.0123 0.4571 1.0000
5.000 0.7023 0.02455 0.01299 -0.0114 0.4488 1.0000
5.250 0.7246 0.02495 0.01343 -0.0105 0.4412 1.0000
5.500 0.7455 0.02556 0.01421 -0.0097 0.4321 1.0000
5.750 0.7678 0.02598 0.01469 -0.0087 0.4247 1.0000
6.000 0.7886 0.02656 0.01544 -0.0078 0.4152 1.0000
6.250 0.8094 0.02714 0.01618 -0.0069 0.4061 1.0000
6.500 0.8320 0.02748 0.01669 -0.0059 0.3980 1.0000
6.750 0.8513 0.02818 0.01762 -0.0049 0.3875 1.0000
7.000 0.8717 0.02878 0.01841 -0.0040 0.3781 1.0000
7.250 0.8941 0.02913 0.01886 -0.0030 0.3698 1.0000
7.500 0.9123 0.02995 0.01996 -0.0020 0.3594 1.0000
7.750 0.9318 0.03065 0.02088 -0.0010 0.3502 1.0000
8.000 0.9534 0.03110 0.02149 0.0001 0.3419 1.0000
8.250 0.9703 0.03187 0.02253 0.0012 0.3303 1.0000
8.500 0.9875 0.03243 0.02345 0.0025 0.3177 1.0000
8.750 1.0042 0.03256 0.02373 0.0042 0.3011 1.0000
9.000 1.0159 0.03291 0.02427 0.0060 0.2800 1.0000
9.250 1.0248 0.03334 0.02479 0.0080 0.2546 1.0000
9.500 1.0267 0.03433 0.02580 0.0101 0.2190 1.0000
9.750 1.0237 0.03597 0.02730 0.0121 0.1779 1.0000
10.000 1.0161 0.03810 0.02929 0.0142 0.1430 1.0000
10.250 1.0044 0.04090 0.03195 0.0156 0.1160 1.0000
10.500 0.9907 0.04455 0.03546 0.0156 0.0946 1.0000
10.750 0.9774 0.04866 0.03950 0.0149 0.0805 1.0000
11.000 0.9648 0.05303 0.04381 0.0139 0.0704 1.0000
11.250 0.9535 0.05741 0.04819 0.0127 0.0643 1.0000
11.500 0.9432 0.06182 0.05261 0.0115 0.0590 1.0000
11.750 0.9324 0.06639 0.05715 0.0102 0.0554 1.0000
12.000 0.9259 0.07047 0.06128 0.0091 0.0521 1.0000
12.250 0.9203 0.07446 0.06536 0.0081 0.0491 1.0000
12.500 0.9154 0.07843 0.06937 0.0070 0.0467 1.0000
12.750 0.9093 0.08259 0.07355 0.0058 0.0442 1.0000
13.000 0.9071 0.08618 0.07713 0.0051 0.0426 1.0000
13.250 0.9082 0.08946 0.08059 0.0046 0.0409 1.0000
13.500 0.9100 0.09276 0.08405 0.0041 0.0393 1.0000
13.750 0.9116 0.09620 0.08764 0.0036 0.0379 1.0000
14.000 0.9123 0.09989 0.09157 0.0028 0.0364 1.0000
14.250 0.9122 0.10380 0.09560 0.0017 0.0350 1.0000
14.500 0.9115 0.10775 0.09959 0.0004 0.0334 1.0000
14.750 0.9101 0.11198 0.10385 -0.0009 0.0321 1.0000
15.000 0.9059 0.11737 0.10947 -0.0032 0.0316 1.0000
15.250 0.8983 0.12374 0.11606 -0.0063 0.0311 1.0000
15.500 0.8888 0.13081 0.12333 -0.0098 0.0309 1.0000
15.750 0.8792 0.13822 0.13089 -0.0137 0.0311 1.0000
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Polar data table (+)
Polar graphs
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