NACA 0006 (naca0006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0006 (naca0006-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.29 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0006-il-1000000-n5.txt Download as CSV file: xf-naca0006-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0006
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.7609 0.10411 0.10261 0.0308 1.0000 0.0022
-10.000 -0.7705 0.09706 0.09558 0.0271 1.0000 0.0022
-9.000 -0.9288 0.02619 0.02303 -0.0075 1.0000 0.0020
-8.750 -0.9135 0.02296 0.01936 -0.0067 1.0000 0.0021
-8.500 -0.8941 0.02079 0.01687 -0.0060 1.0000 0.0022
-8.250 -0.8726 0.01917 0.01498 -0.0054 1.0000 0.0022
-8.000 -0.8500 0.01785 0.01344 -0.0049 1.0000 0.0023
-7.750 -0.8291 0.01587 0.01114 -0.0041 1.0000 0.0024
-7.500 -0.8054 0.01479 0.00990 -0.0036 1.0000 0.0026
-7.250 -0.7804 0.01415 0.00918 -0.0033 1.0000 0.0027
-7.000 -0.7550 0.01361 0.00857 -0.0031 1.0000 0.0030
-6.750 -0.7297 0.01298 0.00785 -0.0027 1.0000 0.0032
-6.500 -0.7045 0.01230 0.00705 -0.0024 1.0000 0.0035
-6.250 -0.6791 0.01166 0.00628 -0.0020 1.0000 0.0037
-6.000 -0.6533 0.01116 0.00569 -0.0017 1.0000 0.0039
-5.750 -0.6281 0.01043 0.00485 -0.0012 1.0000 0.0044
-5.500 -0.6022 0.00999 0.00438 -0.0009 1.0000 0.0049
-5.250 -0.5760 0.00962 0.00396 -0.0007 1.0000 0.0055
-5.000 -0.5497 0.00930 0.00359 -0.0004 1.0000 0.0061
-4.750 -0.5235 0.00891 0.00315 -0.0001 1.0000 0.0076
-4.500 -0.4973 0.00860 0.00283 0.0002 1.0000 0.0093
-4.250 -0.4709 0.00834 0.00254 0.0005 1.0000 0.0119
-4.000 -0.4446 0.00808 0.00232 0.0008 1.0000 0.0185
-3.750 -0.4184 0.00786 0.00213 0.0011 1.0000 0.0267
-3.500 -0.3921 0.00773 0.00198 0.0014 1.0000 0.0294
-3.250 -0.3659 0.00760 0.00184 0.0017 1.0000 0.0309
-3.000 -0.3400 0.00741 0.00165 0.0021 1.0000 0.0349
-2.750 -0.3124 0.00725 0.00149 0.0021 0.9991 0.0380
-2.500 -0.2787 0.00710 0.00134 0.0008 0.9953 0.0416
-2.250 -0.2462 0.00684 0.00120 -0.0004 0.9895 0.0674
-2.000 -0.2136 0.00655 0.00105 -0.0016 0.9818 0.1102
-1.750 -0.1814 0.00624 0.00093 -0.0027 0.9708 0.1646
-1.500 -0.1505 0.00598 0.00083 -0.0035 0.9547 0.2154
-1.250 -0.1230 0.00569 0.00073 -0.0034 0.9315 0.2835
-1.000 -0.0978 0.00548 0.00066 -0.0028 0.9011 0.3447
-0.750 -0.0735 0.00538 0.00059 -0.0019 0.8552 0.3997
-0.500 -0.0501 0.00537 0.00052 -0.0009 0.7729 0.4727
-0.250 -0.0256 0.00534 0.00049 -0.0004 0.6897 0.5579
0.000 0.0000 0.00531 0.00048 0.0000 0.6269 0.6278
0.250 0.0258 0.00534 0.00049 0.0003 0.5580 0.6890
0.500 0.0503 0.00538 0.00052 0.0009 0.4723 0.7716
0.750 0.0737 0.00539 0.00059 0.0019 0.3987 0.8537
1.000 0.0979 0.00549 0.00066 0.0028 0.3426 0.9009
1.250 0.1232 0.00568 0.00073 0.0034 0.2847 0.9315
1.500 0.1506 0.00598 0.00083 0.0034 0.2152 0.9547
1.750 0.1815 0.00624 0.00093 0.0027 0.1641 0.9708
2.000 0.2136 0.00655 0.00105 0.0016 0.1104 0.9819
2.250 0.2462 0.00684 0.00119 0.0004 0.0681 0.9897
2.500 0.2786 0.00710 0.00134 -0.0007 0.0416 0.9955
2.750 0.3123 0.00725 0.00149 -0.0021 0.0380 0.9992
3.000 0.3398 0.00741 0.00165 -0.0021 0.0350 1.0000
3.250 0.3657 0.00760 0.00184 -0.0017 0.0309 1.0000
3.500 0.3919 0.00773 0.00198 -0.0013 0.0294 1.0000
3.750 0.4182 0.00786 0.00213 -0.0010 0.0267 1.0000
4.000 0.4445 0.00808 0.00232 -0.0008 0.0186 1.0000
4.250 0.4707 0.00834 0.00254 -0.0005 0.0118 1.0000
4.500 0.4971 0.00860 0.00283 -0.0002 0.0093 1.0000
4.750 0.5234 0.00891 0.00315 0.0001 0.0076 1.0000
5.000 0.5496 0.00931 0.00360 0.0004 0.0061 1.0000
5.250 0.5760 0.00962 0.00396 0.0007 0.0055 1.0000
5.500 0.6022 0.00999 0.00438 0.0009 0.0049 1.0000
5.750 0.6282 0.01042 0.00485 0.0012 0.0044 1.0000
6.000 0.6534 0.01115 0.00568 0.0016 0.0039 1.0000
6.250 0.6792 0.01166 0.00628 0.0019 0.0037 1.0000
6.500 0.7047 0.01231 0.00706 0.0023 0.0035 1.0000
6.750 0.7299 0.01299 0.00786 0.0027 0.0032 1.0000
7.000 0.7553 0.01359 0.00855 0.0030 0.0030 1.0000
7.250 0.7807 0.01414 0.00916 0.0033 0.0027 1.0000
7.500 0.8057 0.01480 0.00990 0.0035 0.0026 1.0000
7.750 0.8293 0.01588 0.01115 0.0040 0.0024 1.0000
8.000 0.8503 0.01787 0.01346 0.0048 0.0023 1.0000
8.250 0.8730 0.01919 0.01500 0.0053 0.0022 1.0000
8.500 0.8945 0.02082 0.01690 0.0059 0.0022 1.0000
8.750 0.9139 0.02301 0.01941 0.0066 0.0021 1.0000
9.000 0.9294 0.02621 0.02305 0.0074 0.0020 1.0000
10.000 0.7711 0.09730 0.09583 -0.0275 0.0022 1.0000
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Polar data table (+)
Polar graphs
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