EH 2.5/10 (eh2510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.5/10 (eh2510-il) Reynolds number: 1,000,000 Max Cl/Cd: 111.79 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2510-il-1000000.txt Download as CSV file: xf-eh2510-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4314 0.08163 0.08026 -0.0044 1.0000 0.0120
-9.000 -0.4333 0.07712 0.07576 -0.0062 1.0000 0.0125
-8.750 -0.4397 0.07177 0.07043 -0.0086 1.0000 0.0126
-8.500 -0.4533 0.06545 0.06414 -0.0118 1.0000 0.0123
-8.250 -0.4730 0.05948 0.05818 -0.0168 1.0000 0.0123
-8.000 -0.4968 0.05460 0.05328 -0.0180 1.0000 0.0123
-7.750 -0.5883 0.04845 0.04665 -0.0200 1.0000 0.0099
-7.500 -0.6455 0.02535 0.02222 -0.0137 1.0000 0.0100
-7.250 -0.6250 0.02427 0.02095 -0.0126 1.0000 0.0103
-7.000 -0.6116 0.01910 0.01512 -0.0116 0.9787 0.0111
-6.750 -0.5661 0.01834 0.01421 -0.0158 0.9192 0.0118
-6.500 -0.5444 0.01801 0.01364 -0.0146 0.8620 0.0123
-6.250 -0.5240 0.01684 0.01214 -0.0131 0.8245 0.0126
-6.000 -0.5014 0.01596 0.01100 -0.0120 0.7933 0.0130
-5.750 -0.4781 0.01499 0.00977 -0.0110 0.7661 0.0134
-5.500 -0.4538 0.01426 0.00884 -0.0102 0.7420 0.0139
-5.250 -0.4283 0.01388 0.00830 -0.0097 0.7210 0.0144
-5.000 -0.4024 0.01353 0.00780 -0.0091 0.7013 0.0147
-4.750 -0.3785 0.01237 0.00642 -0.0083 0.6843 0.0151
-4.500 -0.3551 0.01132 0.00521 -0.0073 0.6688 0.0157
-4.250 -0.3303 0.01075 0.00452 -0.0066 0.6542 0.0162
-4.000 -0.3050 0.01032 0.00400 -0.0060 0.6400 0.0168
-3.750 -0.2792 0.00999 0.00358 -0.0055 0.6265 0.0174
-3.500 -0.2531 0.00972 0.00324 -0.0051 0.6134 0.0183
-3.250 -0.2268 0.00948 0.00293 -0.0047 0.6010 0.0195
-3.000 -0.2003 0.00927 0.00264 -0.0042 0.5891 0.0204
-2.750 -0.1739 0.00905 0.00233 -0.0038 0.5778 0.0214
-2.250 -0.1212 0.00859 0.00183 -0.0030 0.5562 0.0373
-2.000 -0.0948 0.00840 0.00170 -0.0027 0.5466 0.0614
-1.750 -0.0679 0.00830 0.00160 -0.0024 0.5368 0.0769
-1.500 -0.0410 0.00816 0.00150 -0.0022 0.5269 0.0974
-1.250 -0.0142 0.00803 0.00142 -0.0020 0.5175 0.1227
-1.000 0.0122 0.00787 0.00134 -0.0017 0.5083 0.1637
-0.750 0.0375 0.00755 0.00126 -0.0013 0.4993 0.2482
-0.500 0.0487 0.00594 0.00107 0.0015 0.4924 0.6845
-0.250 0.0687 0.00556 0.00111 0.0034 0.4842 0.8166
0.000 0.0943 0.00552 0.00112 0.0041 0.4760 0.8539
0.250 0.1205 0.00552 0.00114 0.0047 0.4680 0.8775
0.500 0.1470 0.00553 0.00116 0.0052 0.4603 0.8988
1.000 0.2011 0.00561 0.00121 0.0060 0.4445 0.9276
1.250 0.2285 0.00569 0.00127 0.0063 0.4368 0.9429
1.500 0.2562 0.00576 0.00132 0.0065 0.4292 0.9548
1.750 0.2887 0.00588 0.00140 0.0057 0.4218 0.9638
2.000 0.3226 0.00599 0.00148 0.0046 0.4140 0.9711
2.250 0.3595 0.00611 0.00155 0.0026 0.4060 0.9741
2.500 0.3933 0.00620 0.00160 0.0013 0.3981 0.9760
2.750 0.4261 0.00629 0.00165 0.0002 0.3905 0.9783
3.000 0.4555 0.00639 0.00171 -0.0002 0.3830 0.9820
3.250 0.4907 0.00647 0.00177 -0.0018 0.3755 0.9831
3.750 0.5600 0.00665 0.00190 -0.0050 0.3605 0.9857
4.000 0.5937 0.00677 0.00198 -0.0064 0.3526 0.9874
4.250 0.6270 0.00685 0.00205 -0.0076 0.3448 0.9893
4.500 0.6593 0.00696 0.00215 -0.0087 0.3372 0.9915
4.750 0.6908 0.00706 0.00225 -0.0096 0.3301 0.9936
5.000 0.7242 0.00717 0.00235 -0.0110 0.3226 0.9949
5.250 0.7577 0.00728 0.00245 -0.0124 0.3139 0.9963
5.500 0.7910 0.00738 0.00256 -0.0137 0.3063 0.9978
5.750 0.8239 0.00754 0.00268 -0.0150 0.2965 0.9993
6.000 0.8531 0.00768 0.00280 -0.0156 0.2841 1.0000
6.250 0.8754 0.00784 0.00294 -0.0146 0.2709 1.0000
6.500 0.8977 0.00803 0.00310 -0.0137 0.2574 1.0000
6.750 0.9196 0.00827 0.00329 -0.0127 0.2414 1.0000
7.000 0.9416 0.00852 0.00349 -0.0117 0.2246 1.0000
7.250 0.9629 0.00888 0.00376 -0.0107 0.2020 1.0000
7.500 0.9832 0.00934 0.00409 -0.0096 0.1737 1.0000
7.750 1.0024 0.00993 0.00452 -0.0083 0.1397 1.0000
8.000 1.0186 0.01085 0.00516 -0.0067 0.0935 1.0000
8.250 1.0316 0.01209 0.00608 -0.0047 0.0394 1.0000
8.500 1.0482 0.01298 0.00684 -0.0031 0.0173 1.0000
8.750 1.0679 0.01357 0.00745 -0.0020 0.0125 1.0000
9.000 1.0861 0.01429 0.00821 -0.0006 0.0093 1.0000
9.250 1.1069 0.01474 0.00870 0.0004 0.0082 1.0000
9.500 1.1253 0.01540 0.00939 0.0017 0.0069 1.0000
9.750 1.1407 0.01631 0.01042 0.0033 0.0062 1.0000
10.000 1.1594 0.01689 0.01106 0.0045 0.0059 1.0000
10.250 1.1765 0.01757 0.01181 0.0058 0.0055 1.0000
10.500 1.1930 0.01827 0.01258 0.0072 0.0052 1.0000
10.750 1.2071 0.01909 0.01347 0.0088 0.0050 1.0000
11.000 1.2199 0.01993 0.01438 0.0105 0.0048 1.0000
11.250 1.2300 0.02087 0.01539 0.0124 0.0046 1.0000
11.500 1.2294 0.02204 0.01665 0.0159 0.0044 1.0000
11.750 1.2225 0.02373 0.01846 0.0191 0.0043 1.0000
12.000 1.2160 0.02607 0.02093 0.0206 0.0042 1.0000
12.250 1.2095 0.02909 0.02408 0.0208 0.0040 1.0000
12.500 1.2115 0.03160 0.02669 0.0203 0.0039 1.0000
12.750 1.2143 0.03418 0.02938 0.0197 0.0038 1.0000
13.000 1.2097 0.03765 0.03296 0.0188 0.0039 1.0000
13.250 1.2088 0.04076 0.03617 0.0180 0.0038 1.0000
13.500 1.2058 0.04413 0.03965 0.0170 0.0038 1.0000
13.750 1.2016 0.04767 0.04329 0.0161 0.0037 1.0000
14.000 1.1962 0.05133 0.04704 0.0151 0.0036 1.0000
14.250 1.1904 0.05506 0.05086 0.0141 0.0036 1.0000
14.500 1.1830 0.05896 0.05486 0.0131 0.0036 1.0000
14.750 1.1764 0.06289 0.05889 0.0120 0.0036 1.0000
15.000 1.1716 0.06683 0.06292 0.0107 0.0034 1.0000
15.250 1.1650 0.07097 0.06716 0.0095 0.0034 1.0000
15.500 1.1584 0.07525 0.07154 0.0081 0.0034 1.0000
15.750 1.1520 0.07953 0.07591 0.0067 0.0034 1.0000
16.000 1.1437 0.08420 0.08070 0.0051 0.0034 1.0000
16.250 1.1370 0.08875 0.08535 0.0035 0.0034 1.0000
16.500 1.1276 0.09374 0.09046 0.0017 0.0034 1.0000
16.750 1.1205 0.09866 0.09547 -0.0003 0.0034 1.0000
17.000 1.1089 0.10434 0.10128 -0.0026 0.0035 1.0000
17.250 1.0976 0.11022 0.10729 -0.0052 0.0035 1.0000
17.500 1.0849 0.11655 0.11375 -0.0081 0.0035 1.0000
17.750 1.0707 0.12343 0.12076 -0.0114 0.0035 1.0000
18.000 1.0585 0.13008 0.12752 -0.0147 0.0035 1.0000
18.250 1.0459 0.13708 0.13465 -0.0184 0.0036 1.0000
18.500 1.0345 0.14408 0.14175 -0.0222 0.0036 1.0000
18.750 1.0216 0.15165 0.14943 -0.0264 0.0037 1.0000
19.000 1.0045 0.16060 0.15851 -0.0314 0.0037 1.0000
19.250 0.9843 0.17090 0.16894 -0.0371 0.0038 1.0000
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Polar data table (+)
Polar graphs
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