EH 0.0/9.0 (eh0009-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 0.0/9.0 (eh0009-il) Reynolds number: 200,000 Max Cl/Cd: 47.7 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh0009-il-200000.txt Download as CSV file: xf-eh0009-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EH 0.0/9.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6738 0.08718 0.08386 -0.0061 1.0000 0.0574
-9.500 -0.6850 0.08025 0.07698 -0.0115 1.0000 0.0582
-9.250 -0.7791 0.05756 0.05377 -0.0239 1.0000 0.0266
-9.000 -0.7904 0.05390 0.04980 -0.0227 1.0000 0.0277
-8.750 -0.7986 0.04896 0.04464 -0.0216 1.0000 0.0265
-8.500 -0.8016 0.04433 0.03966 -0.0201 1.0000 0.0257
-8.250 -0.7976 0.04060 0.03552 -0.0184 1.0000 0.0264
-8.000 -0.7915 0.03635 0.03081 -0.0165 1.0000 0.0259
-7.750 -0.7815 0.03212 0.02607 -0.0144 1.0000 0.0250
-7.500 -0.7665 0.02869 0.02217 -0.0126 1.0000 0.0249
-7.250 -0.7478 0.02594 0.01902 -0.0110 1.0000 0.0255
-7.000 -0.7269 0.02373 0.01649 -0.0096 1.0000 0.0267
-6.750 -0.7044 0.02267 0.01512 -0.0085 1.0000 0.0291
-6.500 -0.6853 0.01989 0.01226 -0.0072 1.0000 0.0323
-6.250 -0.6642 0.01853 0.01084 -0.0059 1.0000 0.0357
-6.000 -0.6426 0.01745 0.00962 -0.0045 1.0000 0.0398
-5.750 -0.6243 0.01608 0.00829 -0.0029 1.0000 0.0486
-5.500 -0.6050 0.01497 0.00718 -0.0014 1.0000 0.0619
-5.250 -0.5872 0.01369 0.00613 0.0003 1.0000 0.0985
-5.000 -0.5692 0.01257 0.00540 0.0017 1.0000 0.1701
-4.750 -0.5497 0.01181 0.00492 0.0029 1.0000 0.2399
-4.500 -0.5296 0.01121 0.00458 0.0041 1.0000 0.3032
-4.250 -0.5092 0.01071 0.00429 0.0054 1.0000 0.3637
-4.000 -0.4892 0.01025 0.00407 0.0067 1.0000 0.4258
-3.750 -0.4689 0.00989 0.00389 0.0082 1.0000 0.4795
-3.500 -0.4483 0.00960 0.00373 0.0096 1.0000 0.5280
-3.250 -0.4279 0.00934 0.00359 0.0111 1.0000 0.5731
-3.000 -0.4076 0.00912 0.00352 0.0127 1.0000 0.6170
-2.750 -0.3875 0.00895 0.00347 0.0143 1.0000 0.6580
-2.500 -0.3676 0.00883 0.00346 0.0160 1.0000 0.6967
-2.250 -0.3480 0.00876 0.00349 0.0177 1.0000 0.7344
-2.000 -0.3291 0.00871 0.00355 0.0197 1.0000 0.7692
-1.750 -0.3108 0.00871 0.00361 0.0217 1.0000 0.8034
-1.500 -0.2915 0.00875 0.00373 0.0235 0.9995 0.8362
-1.250 -0.2494 0.00888 0.00391 0.0208 0.9911 0.8690
-1.000 -0.2055 0.00902 0.00405 0.0179 0.9833 0.8971
-0.750 -0.1599 0.00914 0.00416 0.0146 0.9755 0.9188
-0.500 -0.1076 0.00927 0.00427 0.0100 0.9697 0.9355
-0.250 -0.0555 0.00935 0.00434 0.0053 0.9628 0.9479
0.000 0.0000 0.00938 0.00436 0.0000 0.9568 0.9568
0.250 0.0555 0.00935 0.00434 -0.0053 0.9479 0.9629
0.500 0.1077 0.00927 0.00427 -0.0100 0.9356 0.9698
0.750 0.1599 0.00914 0.00416 -0.0146 0.9190 0.9756
1.000 0.2055 0.00902 0.00404 -0.0179 0.8970 0.9833
1.250 0.2494 0.00888 0.00390 -0.0208 0.8692 0.9912
1.500 0.2915 0.00874 0.00373 -0.0235 0.8365 0.9996
1.750 0.3106 0.00871 0.00361 -0.0216 0.8035 1.0000
2.000 0.3288 0.00871 0.00355 -0.0196 0.7692 1.0000
2.250 0.3477 0.00875 0.00348 -0.0177 0.7344 1.0000
2.500 0.3673 0.00883 0.00346 -0.0159 0.6969 1.0000
2.750 0.3872 0.00895 0.00347 -0.0142 0.6582 1.0000
3.000 0.4073 0.00912 0.00351 -0.0126 0.6172 1.0000
3.250 0.4276 0.00933 0.00359 -0.0110 0.5734 1.0000
3.500 0.4480 0.00960 0.00373 -0.0095 0.5282 1.0000
3.750 0.4686 0.00989 0.00389 -0.0081 0.4796 1.0000
4.000 0.4889 0.01025 0.00407 -0.0067 0.4262 1.0000
4.250 0.5089 0.01070 0.00429 -0.0053 0.3643 1.0000
4.500 0.5293 0.01120 0.00457 -0.0040 0.3035 1.0000
4.750 0.5494 0.01181 0.00492 -0.0028 0.2399 1.0000
5.000 0.5689 0.01257 0.00540 -0.0016 0.1704 1.0000
5.250 0.5870 0.01369 0.00613 -0.0002 0.0985 1.0000
5.500 0.6049 0.01497 0.00718 0.0014 0.0621 1.0000
5.750 0.6242 0.01607 0.00828 0.0030 0.0486 1.0000
6.000 0.6426 0.01744 0.00962 0.0045 0.0398 1.0000
6.250 0.6642 0.01852 0.01083 0.0059 0.0356 1.0000
6.500 0.6854 0.01988 0.01225 0.0072 0.0323 1.0000
6.750 0.7043 0.02275 0.01520 0.0085 0.0291 1.0000
7.000 0.7270 0.02374 0.01650 0.0096 0.0267 1.0000
7.250 0.7480 0.02593 0.01900 0.0110 0.0255 1.0000
7.500 0.7667 0.02870 0.02217 0.0126 0.0249 1.0000
7.750 0.7816 0.03216 0.02612 0.0144 0.0250 1.0000
8.000 0.7918 0.03630 0.03076 0.0164 0.0259 1.0000
8.250 0.7972 0.04083 0.03574 0.0183 0.0268 1.0000
8.500 0.8006 0.04474 0.04006 0.0200 0.0264 1.0000
8.750 0.7982 0.04923 0.04489 0.0215 0.0269 1.0000
9.000 0.7920 0.05336 0.04933 0.0228 0.0267 1.0000
9.250 0.7796 0.05801 0.05415 0.0236 0.0276 1.0000
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Polar data table (+)
Polar graphs
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