NACA 0008-34 (naca000834-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0008-34 (naca000834-il) Reynolds number: 1,000,000 Max Cl/Cd: 42.99 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca000834-il-1000000.txt Download as CSV file: xf-naca000834-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0008-34
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6711 0.08448 0.08297 -0.0083 1.0000 0.0053
-9.250 -0.6737 0.07614 0.07462 -0.0175 1.0000 0.0052
-9.000 -0.6815 0.07058 0.06899 -0.0217 1.0000 0.0052
-8.750 -0.6921 0.06625 0.06458 -0.0223 1.0000 0.0052
-8.500 -0.7032 0.06112 0.05933 -0.0224 1.0000 0.0052
-8.250 -0.7104 0.05604 0.05410 -0.0219 1.0000 0.0053
-8.000 -0.7131 0.05148 0.04937 -0.0208 1.0000 0.0054
-7.750 -0.7114 0.04748 0.04520 -0.0194 1.0000 0.0055
-7.500 -0.7064 0.04413 0.04168 -0.0177 1.0000 0.0057
-7.250 -0.6994 0.04133 0.03870 -0.0158 1.0000 0.0058
-7.000 -0.6919 0.03855 0.03575 -0.0134 1.0000 0.0060
-6.750 -0.6836 0.03589 0.03290 -0.0108 1.0000 0.0063
-6.500 -0.6747 0.03333 0.03015 -0.0079 1.0000 0.0066
-6.250 -0.6649 0.03087 0.02749 -0.0049 1.0000 0.0071
-6.000 -0.6530 0.02861 0.02502 -0.0018 1.0000 0.0079
-5.500 -0.6243 0.02205 0.01778 0.0041 0.9994 0.0082
-5.250 -0.5954 0.01938 0.01480 0.0040 0.9981 0.0084
-5.000 -0.5662 0.01673 0.01184 0.0039 0.9969 0.0082
-4.750 -0.5341 0.01581 0.01079 0.0029 0.9957 0.0089
-4.500 -0.5042 0.01352 0.00829 0.0026 0.9948 0.0086
-4.250 -0.4747 0.01179 0.00640 0.0024 0.9937 0.0085
-4.000 -0.4462 0.01067 0.00518 0.0022 0.9915 0.0089
-3.750 -0.4152 0.01005 0.00450 0.0014 0.9892 0.0099
-3.500 -0.3852 0.00896 0.00326 0.0007 0.9870 0.0122
-3.250 -0.3517 0.00860 0.00286 -0.0008 0.9854 0.0145
-3.000 -0.3171 0.00832 0.00254 -0.0024 0.9840 0.0174
-2.750 -0.2823 0.00786 0.00205 -0.0041 0.9827 0.0345
-2.500 -0.2573 0.00654 0.00164 -0.0043 0.9787 0.2772
-2.250 -0.2321 0.00550 0.00139 -0.0045 0.9739 0.4913
-2.000 -0.2047 0.00485 0.00124 -0.0048 0.9699 0.6295
-1.750 -0.1817 0.00439 0.00116 -0.0037 0.9631 0.7401
-1.500 -0.1568 0.00414 0.00112 -0.0029 0.9569 0.8052
-1.250 -0.1310 0.00405 0.00109 -0.0024 0.9499 0.8330
-1.000 -0.1051 0.00396 0.00106 -0.0018 0.9430 0.8570
-0.750 -0.0790 0.00392 0.00104 -0.0013 0.9349 0.8717
-0.500 -0.0526 0.00389 0.00101 -0.0009 0.9274 0.8858
-0.250 -0.0264 0.00387 0.00101 -0.0004 0.9180 0.8980
0.000 0.0000 0.00387 0.00101 0.0000 0.9084 0.9084
0.250 0.0264 0.00387 0.00101 0.0004 0.8981 0.9180
0.500 0.0525 0.00389 0.00101 0.0009 0.8859 0.9274
0.750 0.0790 0.00392 0.00104 0.0013 0.8718 0.9350
1.000 0.1051 0.00396 0.00106 0.0018 0.8570 0.9430
1.250 0.1310 0.00405 0.00109 0.0024 0.8335 0.9499
1.500 0.1567 0.00414 0.00112 0.0029 0.8049 0.9569
1.750 0.1817 0.00439 0.00116 0.0037 0.7406 0.9631
2.000 0.2046 0.00486 0.00124 0.0048 0.6285 0.9699
2.250 0.2321 0.00550 0.00139 0.0045 0.4907 0.9739
2.500 0.2573 0.00653 0.00164 0.0044 0.2794 0.9787
2.750 0.2823 0.00785 0.00204 0.0041 0.0356 0.9827
3.000 0.3170 0.00832 0.00253 0.0025 0.0174 0.9840
3.250 0.3516 0.00860 0.00286 0.0008 0.0145 0.9854
3.500 0.3852 0.00896 0.00326 -0.0007 0.0122 0.9871
3.750 0.4153 0.01004 0.00448 -0.0014 0.0099 0.9893
4.000 0.4462 0.01067 0.00518 -0.0022 0.0089 0.9915
4.250 0.4746 0.01179 0.00639 -0.0024 0.0085 0.9938
4.500 0.5041 0.01352 0.00828 -0.0026 0.0086 0.9948
4.750 0.5340 0.01584 0.01083 -0.0029 0.0090 0.9957
5.000 0.5662 0.01669 0.01180 -0.0039 0.0082 0.9969
5.250 0.5954 0.01936 0.01477 -0.0040 0.0084 0.9981
5.500 0.6241 0.02214 0.01789 -0.0041 0.0082 0.9995
6.000 0.6529 0.02860 0.02501 0.0018 0.0079 1.0000
6.250 0.6648 0.03087 0.02749 0.0049 0.0071 1.0000
6.500 0.6747 0.03334 0.03016 0.0079 0.0066 1.0000
6.750 0.6836 0.03589 0.03291 0.0108 0.0063 1.0000
7.000 0.6919 0.03855 0.03575 0.0134 0.0060 1.0000
7.250 0.6994 0.04132 0.03868 0.0158 0.0058 1.0000
7.500 0.7065 0.04414 0.04169 0.0177 0.0057 1.0000
7.750 0.7115 0.04749 0.04521 0.0194 0.0055 1.0000
8.000 0.7132 0.05150 0.04939 0.0208 0.0054 1.0000
8.250 0.7106 0.05606 0.05412 0.0218 0.0053 1.0000
8.500 0.7034 0.06115 0.05936 0.0223 0.0052 1.0000
8.750 0.6922 0.06632 0.06465 0.0222 0.0052 1.0000
9.000 0.6816 0.07068 0.06909 0.0215 0.0052 1.0000
9.250 0.6743 0.07623 0.07471 0.0173 0.0052 1.0000
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Polar data table (+)
Polar graphs
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