NACA 0006 (naca0006-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 0006 (naca0006-il) Reynolds number: 100,000 Max Cl/Cd: 27.26 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0006-il-100000-n5.txt Download as CSV file: xf-naca0006-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6995 0.10224 0.09745 0.0211 1.0000 0.0229
-9.000 -0.7022 0.09655 0.09181 0.0176 1.0000 0.0221
-8.750 -0.7090 0.08879 0.08413 0.0114 1.0000 0.0208
-8.250 -0.7104 0.07387 0.06910 -0.0025 1.0000 0.0191
-8.000 -0.7123 0.06820 0.06332 -0.0054 1.0000 0.0190
-7.750 -0.7120 0.06261 0.05755 -0.0076 1.0000 0.0189
-7.500 -0.7090 0.05714 0.05184 -0.0091 1.0000 0.0188
-7.250 -0.7031 0.05182 0.04619 -0.0099 1.0000 0.0187
-7.000 -0.6940 0.04670 0.04066 -0.0102 1.0000 0.0187
-6.750 -0.6816 0.04192 0.03538 -0.0101 1.0000 0.0187
-6.500 -0.6661 0.03759 0.03047 -0.0095 1.0000 0.0189
-6.250 -0.6476 0.03385 0.02611 -0.0087 1.0000 0.0192
-6.000 -0.6294 0.03014 0.02202 -0.0082 1.0000 0.0207
-5.750 -0.6074 0.02824 0.01985 -0.0077 1.0000 0.0233
-5.500 -0.5836 0.02570 0.01686 -0.0068 1.0000 0.0252
-5.250 -0.5588 0.02335 0.01410 -0.0059 1.0000 0.0273
-5.000 -0.5342 0.02158 0.01202 -0.0051 1.0000 0.0316
-4.750 -0.5101 0.02008 0.01042 -0.0044 1.0000 0.0363
-4.500 -0.4864 0.01870 0.00895 -0.0036 1.0000 0.0439
-4.250 -0.4623 0.01759 0.00772 -0.0028 1.0000 0.0529
-4.000 -0.4381 0.01668 0.00675 -0.0022 1.0000 0.0665
-3.750 -0.4138 0.01581 0.00576 -0.0015 1.0000 0.0788
-3.500 -0.3897 0.01491 0.00501 -0.0010 1.0000 0.1077
-3.250 -0.3665 0.01377 0.00432 -0.0004 1.0000 0.1958
-3.000 -0.3440 0.01274 0.00387 0.0002 1.0000 0.3396
-2.750 -0.3214 0.01195 0.00353 0.0012 1.0000 0.4711
-2.500 -0.3019 0.01107 0.00344 0.0034 1.0000 0.6531
-2.250 -0.2799 0.01060 0.00354 0.0064 1.0000 0.8245
-1.750 -0.1919 0.01053 0.00325 0.0014 1.0000 0.9630
-1.500 -0.1418 0.01045 0.00299 -0.0034 1.0000 0.9909
-1.250 -0.1078 0.01034 0.00275 -0.0050 1.0000 1.0000
-1.000 -0.0859 0.01026 0.00258 -0.0042 1.0000 1.0000
-0.750 -0.0642 0.01020 0.00246 -0.0032 1.0000 1.0000
-0.500 -0.0427 0.01015 0.00237 -0.0022 1.0000 1.0000
-0.250 -0.0213 0.01013 0.00231 -0.0011 1.0000 1.0000
0.000 0.0000 0.01012 0.00230 0.0000 1.0000 1.0000
0.250 0.0213 0.01013 0.00231 0.0011 1.0000 1.0000
0.500 0.0427 0.01015 0.00237 0.0022 1.0000 1.0000
0.750 0.0642 0.01020 0.00246 0.0032 1.0000 1.0000
1.000 0.0859 0.01026 0.00258 0.0042 1.0000 1.0000
1.250 0.1078 0.01034 0.00274 0.0050 1.0000 1.0000
1.500 0.1418 0.01045 0.00299 0.0034 0.9909 1.0000
1.750 0.1919 0.01053 0.00325 -0.0014 0.9631 1.0000
2.250 0.2799 0.01060 0.00354 -0.0064 0.8248 1.0000
2.500 0.3018 0.01107 0.00344 -0.0034 0.6534 1.0000
2.750 0.3213 0.01195 0.00353 -0.0011 0.4714 1.0000
3.000 0.3439 0.01274 0.00387 -0.0002 0.3399 1.0000
3.250 0.3664 0.01377 0.00432 0.0004 0.1960 1.0000
3.500 0.3896 0.01490 0.00501 0.0010 0.1078 1.0000
3.750 0.4137 0.01581 0.00576 0.0015 0.0789 1.0000
4.000 0.4381 0.01668 0.00675 0.0022 0.0665 1.0000
4.250 0.4622 0.01759 0.00772 0.0028 0.0529 1.0000
4.500 0.4863 0.01870 0.00895 0.0036 0.0439 1.0000
4.750 0.5101 0.02008 0.01042 0.0044 0.0363 1.0000
5.000 0.5342 0.02159 0.01202 0.0051 0.0316 1.0000
5.250 0.5588 0.02336 0.01410 0.0058 0.0273 1.0000
5.500 0.5836 0.02570 0.01686 0.0068 0.0252 1.0000
5.750 0.6075 0.02824 0.01985 0.0077 0.0233 1.0000
6.000 0.6295 0.03015 0.02203 0.0082 0.0207 1.0000
6.250 0.6476 0.03386 0.02612 0.0087 0.0192 1.0000
6.500 0.6662 0.03760 0.03048 0.0095 0.0189 1.0000
6.750 0.6817 0.04193 0.03539 0.0100 0.0187 1.0000
7.000 0.6941 0.04672 0.04068 0.0102 0.0187 1.0000
7.250 0.7032 0.05183 0.04621 0.0099 0.0187 1.0000
7.500 0.7092 0.05716 0.05186 0.0090 0.0188 1.0000
7.750 0.7122 0.06264 0.05758 0.0075 0.0189 1.0000
8.000 0.7125 0.06823 0.06335 0.0053 0.0190 1.0000
8.250 0.7107 0.07392 0.06915 0.0024 0.0191 1.0000
8.750 0.6046 0.07599 0.07155 -0.0017 0.0209 1.0000
9.000 0.5924 0.08296 0.07846 -0.0051 0.0216 1.0000
9.250 0.5834 0.08901 0.08447 -0.0076 0.0223 1.0000
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Polar data table (+)
Polar graphs
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