EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.81 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1090-il-1000000.txt Download as CSV file: xf-eh1090-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6162 0.14088 0.13923 0.0240 1.0000 0.0085
-12.250 -0.6125 0.13634 0.13470 0.0221 1.0000 0.0085
-8.000 -0.7698 0.02483 0.02131 -0.0126 1.0000 0.0067
-7.750 -0.7553 0.02208 0.01821 -0.0109 1.0000 0.0069
-7.500 -0.7360 0.02041 0.01632 -0.0097 1.0000 0.0073
-7.250 -0.7156 0.01888 0.01459 -0.0086 1.0000 0.0076
-7.000 -0.6946 0.01748 0.01299 -0.0075 1.0000 0.0078
-6.750 -0.6724 0.01641 0.01177 -0.0065 1.0000 0.0080
-6.500 -0.6509 0.01517 0.01037 -0.0053 1.0000 0.0082
-6.250 -0.6287 0.01426 0.00935 -0.0043 1.0000 0.0083
-6.000 -0.6058 0.01368 0.00867 -0.0033 1.0000 0.0085
-5.750 -0.5856 0.01258 0.00745 -0.0018 1.0000 0.0088
-5.500 -0.5668 0.01139 0.00613 0.0000 1.0000 0.0090
-5.250 -0.5442 0.01037 0.00498 0.0009 0.9991 0.0096
-5.000 -0.5087 0.00973 0.00428 -0.0008 0.9949 0.0108
-4.750 -0.4739 0.00932 0.00384 -0.0024 0.9895 0.0121
-4.500 -0.4381 0.00896 0.00341 -0.0041 0.9833 0.0132
-4.250 -0.4051 0.00849 0.00288 -0.0052 0.9719 0.0168
-4.000 -0.3734 0.00806 0.00252 -0.0060 0.9562 0.0337
-3.750 -0.3462 0.00776 0.00228 -0.0058 0.9333 0.0550
-3.500 -0.3216 0.00753 0.00209 -0.0049 0.9073 0.0786
-3.250 -0.2970 0.00736 0.00190 -0.0042 0.8816 0.1007
-3.000 -0.2721 0.00717 0.00173 -0.0035 0.8563 0.1313
-2.750 -0.2472 0.00691 0.00157 -0.0029 0.8316 0.1795
-2.500 -0.2226 0.00655 0.00141 -0.0024 0.8076 0.2541
-2.250 -0.1979 0.00619 0.00126 -0.0018 0.7844 0.3382
-2.000 -0.1737 0.00578 0.00111 -0.0013 0.7620 0.4419
-1.750 -0.1497 0.00536 0.00100 -0.0006 0.7403 0.5539
-1.500 -0.1247 0.00511 0.00093 -0.0001 0.7196 0.6323
-1.250 -0.0992 0.00494 0.00089 0.0005 0.6992 0.6926
-1.000 -0.0738 0.00482 0.00086 0.0011 0.6794 0.7481
-0.750 -0.0476 0.00477 0.00085 0.0016 0.6603 0.7840
-0.500 -0.0210 0.00476 0.00084 0.0020 0.6411 0.8104
-0.250 0.0059 0.00478 0.00083 0.0023 0.6230 0.8304
0.000 0.0327 0.00480 0.00084 0.0027 0.6057 0.8500
0.250 0.0593 0.00483 0.00085 0.0031 0.5887 0.8700
0.500 0.0855 0.00485 0.00088 0.0037 0.5721 0.8901
0.750 0.1118 0.00490 0.00091 0.0042 0.5555 0.9065
1.000 0.1379 0.00497 0.00095 0.0047 0.5390 0.9217
1.250 0.1639 0.00505 0.00100 0.0054 0.5228 0.9362
1.500 0.1903 0.00513 0.00105 0.0059 0.5072 0.9492
1.750 0.2181 0.00523 0.00112 0.0060 0.4915 0.9596
2.000 0.2456 0.00534 0.00118 0.0063 0.4755 0.9692
2.250 0.2789 0.00546 0.00124 0.0051 0.4568 0.9734
2.500 0.3116 0.00560 0.00130 0.0040 0.4369 0.9776
2.750 0.3419 0.00573 0.00138 0.0035 0.4178 0.9825
3.000 0.3782 0.00585 0.00145 0.0016 0.4014 0.9840
3.250 0.4143 0.00598 0.00152 -0.0003 0.3847 0.9857
3.500 0.4494 0.00610 0.00161 -0.0020 0.3688 0.9879
3.750 0.4834 0.00625 0.00171 -0.0034 0.3491 0.9904
4.000 0.5163 0.00642 0.00182 -0.0046 0.3277 0.9932
4.250 0.5501 0.00663 0.00193 -0.0061 0.2993 0.9950
4.500 0.5839 0.00695 0.00207 -0.0077 0.2551 0.9969
4.750 0.6173 0.00728 0.00226 -0.0092 0.2155 0.9989
5.000 0.6471 0.00763 0.00246 -0.0099 0.1806 1.0000
5.250 0.6682 0.00801 0.00269 -0.0088 0.1447 1.0000
5.500 0.6888 0.00849 0.00299 -0.0077 0.1046 1.0000
5.750 0.7085 0.00910 0.00337 -0.0064 0.0615 1.0000
6.000 0.7270 0.00993 0.00398 -0.0049 0.0177 1.0000
6.250 0.7483 0.01044 0.00451 -0.0037 0.0126 1.0000
6.500 0.7702 0.01090 0.00504 -0.0025 0.0114 1.0000
6.750 0.7928 0.01126 0.00546 -0.0016 0.0107 1.0000
7.000 0.8156 0.01163 0.00585 -0.0007 0.0096 1.0000
7.250 0.8379 0.01207 0.00633 0.0002 0.0086 1.0000
7.500 0.8566 0.01307 0.00746 0.0017 0.0074 1.0000
7.750 0.8756 0.01405 0.00859 0.0031 0.0070 1.0000
8.000 0.8982 0.01455 0.00915 0.0038 0.0067 1.0000
8.250 0.9202 0.01513 0.00980 0.0047 0.0063 1.0000
8.500 0.9410 0.01590 0.01064 0.0056 0.0059 1.0000
8.750 0.9613 0.01671 0.01154 0.0066 0.0055 1.0000
9.000 0.9818 0.01748 0.01237 0.0075 0.0051 1.0000
9.250 1.0002 0.01850 0.01347 0.0087 0.0049 1.0000
9.500 1.0163 0.01981 0.01490 0.0100 0.0047 1.0000
9.750 1.0294 0.02155 0.01679 0.0117 0.0045 1.0000
10.000 1.0385 0.02393 0.01939 0.0138 0.0044 1.0000
10.250 1.0455 0.02652 0.02221 0.0159 0.0043 1.0000
10.500 1.0435 0.03022 0.02623 0.0185 0.0042 1.0000
10.750 1.0452 0.03271 0.02894 0.0208 0.0042 1.0000
11.000 1.0350 0.03541 0.03187 0.0243 0.0042 1.0000
11.250 1.0214 0.03822 0.03488 0.0270 0.0042 1.0000
11.500 1.0058 0.04164 0.03849 0.0282 0.0042 1.0000
11.750 1.0008 0.04428 0.04125 0.0281 0.0042 1.0000
12.000 0.9932 0.04764 0.04474 0.0271 0.0042 1.0000
12.250 0.9849 0.05156 0.04880 0.0253 0.0042 1.0000
12.500 0.9697 0.05697 0.05436 0.0221 0.0042 1.0000
12.750 0.9710 0.06015 0.05761 0.0200 0.0043 1.0000
13.000 0.9545 0.06670 0.06431 0.0157 0.0043 1.0000
13.250 0.9397 0.07333 0.07106 0.0112 0.0043 1.0000
13.500 0.9271 0.08003 0.07786 0.0068 0.0043 1.0000
13.750 0.9233 0.08527 0.08318 0.0033 0.0044 1.0000
14.000 0.8986 0.09525 0.09328 -0.0030 0.0043 1.0000
14.250 0.8927 0.10160 0.09971 -0.0069 0.0044 1.0000
14.500 0.8766 0.11088 0.10908 -0.0124 0.0044 1.0000
14.750 0.8616 0.12051 0.11880 -0.0177 0.0045 1.0000
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Polar data table (+)
Polar graphs
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