NACA 0006 (naca0006-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0006 (naca0006-il) Reynolds number: 200,000 Max Cl/Cd: 34.02 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca0006-il-200000-n5.txt Download as CSV file: xf-naca0006-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7134 0.09053 0.08719 0.0174 1.0000 0.0101
-8.750 -0.7180 0.08461 0.08131 0.0134 1.0000 0.0099
-8.500 -0.7235 0.07795 0.07469 0.0071 1.0000 0.0098
-8.250 -0.7278 0.07039 0.06708 -0.0002 1.0000 0.0097
-8.000 -0.7294 0.06324 0.05979 -0.0048 1.0000 0.0095
-7.750 -0.7287 0.05643 0.05277 -0.0077 1.0000 0.0094
-7.500 -0.7252 0.04986 0.04590 -0.0092 1.0000 0.0093
-7.250 -0.7184 0.04356 0.03920 -0.0098 1.0000 0.0092
-7.000 -0.7082 0.03775 0.03290 -0.0095 1.0000 0.0093
-6.750 -0.6942 0.03274 0.02732 -0.0088 1.0000 0.0094
-6.500 -0.6764 0.02879 0.02281 -0.0079 1.0000 0.0097
-6.250 -0.6563 0.02554 0.01899 -0.0070 1.0000 0.0107
-6.000 -0.6356 0.02250 0.01550 -0.0062 1.0000 0.0118
-5.750 -0.6121 0.02049 0.01316 -0.0054 1.0000 0.0126
-5.500 -0.5878 0.01884 0.01126 -0.0046 1.0000 0.0137
-5.250 -0.5633 0.01747 0.00970 -0.0039 1.0000 0.0155
-5.000 -0.5382 0.01653 0.00854 -0.0033 1.0000 0.0184
-4.750 -0.5146 0.01515 0.00706 -0.0025 1.0000 0.0209
-4.500 -0.4895 0.01446 0.00630 -0.0020 1.0000 0.0267
-4.250 -0.4647 0.01366 0.00541 -0.0015 1.0000 0.0330
-4.000 -0.4395 0.01309 0.00477 -0.0010 1.0000 0.0418
-3.750 -0.4140 0.01260 0.00421 -0.0007 1.0000 0.0514
-3.500 -0.3886 0.01208 0.00367 -0.0002 1.0000 0.0609
-3.250 -0.3631 0.01161 0.00322 0.0002 1.0000 0.0784
-3.000 -0.3386 0.01091 0.00281 0.0005 1.0000 0.1392
-2.750 -0.3143 0.01023 0.00246 0.0009 1.0000 0.2336
-2.500 -0.2902 0.00963 0.00222 0.0013 1.0000 0.3308
-2.250 -0.2663 0.00907 0.00203 0.0019 1.0000 0.4305
-2.000 -0.2434 0.00849 0.00190 0.0028 1.0000 0.5445
-1.750 -0.2215 0.00796 0.00182 0.0041 1.0000 0.6593
-1.500 -0.2012 0.00750 0.00186 0.0063 1.0000 0.7809
-1.250 -0.1752 0.00733 0.00196 0.0078 1.0000 0.8894
-1.000 -0.1343 0.00733 0.00196 0.0055 1.0000 0.9482
-0.750 -0.0933 0.00733 0.00192 0.0027 1.0000 0.9757
-0.500 -0.0509 0.00732 0.00186 -0.0005 1.0000 0.9942
-0.250 -0.0206 0.00729 0.00181 -0.0013 1.0000 1.0000
0.000 0.0000 0.00728 0.00180 0.0000 1.0000 1.0000
0.250 0.0206 0.00729 0.00181 0.0013 1.0000 1.0000
0.500 0.0508 0.00732 0.00186 0.0006 0.9942 1.0000
0.750 0.0933 0.00733 0.00192 -0.0027 0.9757 1.0000
1.000 0.1343 0.00733 0.00196 -0.0055 0.9482 1.0000
1.250 0.1752 0.00733 0.00196 -0.0078 0.8897 1.0000
1.500 0.2011 0.00750 0.00186 -0.0063 0.7812 1.0000
1.750 0.2214 0.00796 0.00182 -0.0041 0.6594 1.0000
2.000 0.2433 0.00849 0.00190 -0.0027 0.5446 1.0000
2.250 0.2662 0.00907 0.00203 -0.0019 0.4310 1.0000
2.500 0.2901 0.00963 0.00222 -0.0013 0.3310 1.0000
3.000 0.3385 0.01091 0.00281 -0.0005 0.1395 1.0000
3.250 0.3630 0.01161 0.00322 -0.0002 0.0784 1.0000
3.500 0.3885 0.01208 0.00367 0.0003 0.0609 1.0000
3.750 0.4140 0.01260 0.00421 0.0007 0.0514 1.0000
4.000 0.4394 0.01309 0.00476 0.0011 0.0418 1.0000
4.250 0.4647 0.01366 0.00541 0.0015 0.0330 1.0000
4.500 0.4895 0.01446 0.00629 0.0020 0.0266 1.0000
4.750 0.5146 0.01515 0.00706 0.0025 0.0209 1.0000
5.000 0.5382 0.01653 0.00854 0.0033 0.0184 1.0000
5.250 0.5633 0.01747 0.00970 0.0039 0.0155 1.0000
5.500 0.5879 0.01884 0.01126 0.0046 0.0137 1.0000
5.750 0.6121 0.02049 0.01316 0.0054 0.0126 1.0000
6.000 0.6356 0.02251 0.01550 0.0062 0.0118 1.0000
6.250 0.6562 0.02559 0.01905 0.0070 0.0106 1.0000
6.500 0.6764 0.02881 0.02283 0.0079 0.0097 1.0000
6.750 0.6943 0.03274 0.02733 0.0088 0.0094 1.0000
7.000 0.7083 0.03777 0.03292 0.0095 0.0093 1.0000
7.250 0.7185 0.04358 0.03923 0.0097 0.0092 1.0000
7.500 0.7253 0.04988 0.04592 0.0092 0.0093 1.0000
7.750 0.7289 0.05646 0.05280 0.0076 0.0094 1.0000
8.000 0.7296 0.06328 0.05983 0.0047 0.0095 1.0000
8.250 0.7280 0.07045 0.06713 0.0001 0.0097 1.0000
8.500 0.7239 0.07801 0.07475 -0.0072 0.0098 1.0000
8.750 0.7185 0.08469 0.08138 -0.0135 0.0099 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0006 (naca0006-il)