NACA 0015 (naca0015-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0015 (naca0015-il) Reynolds number: 50,000 Max Cl/Cd: 24.7 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca0015-il-50000.txt Download as CSV file: xf-naca0015-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8022 0.07748 0.06925 -0.0308 1.0000 0.1885
-10.750 -0.8442 0.07035 0.06203 -0.0311 1.0000 0.1873
-10.500 -0.8851 0.06475 0.05627 -0.0287 1.0000 0.1865
-10.250 -0.9176 0.05969 0.05093 -0.0257 1.0000 0.1869
-10.000 -0.9434 0.05517 0.04599 -0.0220 1.0000 0.1883
-9.750 -0.9165 0.05358 0.04459 -0.0216 1.0000 0.1959
-9.500 -0.9248 0.05030 0.04100 -0.0185 1.0000 0.2010
-9.250 -0.9332 0.04694 0.03723 -0.0150 1.0000 0.2061
-9.000 -0.9132 0.04547 0.03586 -0.0138 1.0000 0.2161
-8.750 -0.9076 0.04310 0.03330 -0.0112 1.0000 0.2249
-8.500 -0.8997 0.04122 0.03122 -0.0086 1.0000 0.2360
-8.250 -0.8818 0.03986 0.02996 -0.0070 1.0000 0.2489
-8.000 -0.8680 0.03838 0.02847 -0.0048 1.0000 0.2627
-7.750 -0.8545 0.03697 0.02703 -0.0026 1.0000 0.2778
-7.500 -0.8402 0.03572 0.02578 -0.0003 1.0000 0.2944
-7.250 -0.8248 0.03461 0.02471 0.0019 1.0000 0.3123
-7.000 -0.8089 0.03359 0.02373 0.0041 1.0000 0.3315
-6.750 -0.7934 0.03263 0.02281 0.0064 1.0000 0.3520
-6.500 -0.7795 0.03164 0.02179 0.0089 1.0000 0.3737
-6.250 -0.7622 0.03086 0.02112 0.0111 1.0000 0.3959
-6.000 -0.7431 0.03032 0.02072 0.0132 1.0000 0.4189
-5.750 -0.7273 0.02963 0.02006 0.0157 1.0000 0.4433
-5.500 -0.7103 0.02904 0.01955 0.0180 1.0000 0.4678
-5.250 -0.6910 0.02869 0.01933 0.0203 1.0000 0.4923
-5.000 -0.6765 0.02808 0.01870 0.0229 1.0000 0.5187
-4.750 -0.6558 0.02790 0.01869 0.0252 1.0000 0.5430
-4.500 -0.6380 0.02761 0.01847 0.0278 1.0000 0.5688
-4.250 -0.6209 0.02729 0.01819 0.0303 1.0000 0.5946
-4.000 -0.6011 0.02725 0.01826 0.0329 1.0000 0.6194
-3.750 -0.5860 0.02691 0.01792 0.0355 1.0000 0.6464
-3.500 -0.5652 0.02701 0.01811 0.0381 1.0000 0.6703
-3.250 -0.5463 0.02705 0.01819 0.0407 1.0000 0.6956
-3.000 -0.5299 0.02694 0.01810 0.0433 1.0000 0.7219
-2.750 -0.5069 0.02726 0.01845 0.0456 1.0000 0.7462
-2.500 -0.4886 0.02733 0.01852 0.0480 1.0000 0.7732
-2.250 -0.4624 0.02772 0.01892 0.0494 1.0000 0.7982
-2.000 -0.4322 0.02817 0.01934 0.0500 1.0000 0.8243
-1.750 -0.3985 0.02859 0.01972 0.0494 1.0000 0.8513
-1.500 -0.3429 0.02935 0.02041 0.0451 1.0000 0.8763
-1.250 -0.2907 0.02981 0.02081 0.0404 1.0000 0.9034
-1.000 -0.2043 0.03039 0.02129 0.0292 1.0000 0.9258
-0.750 -0.1382 0.03057 0.02142 0.0206 1.0000 0.9519
-0.500 -0.0601 0.03056 0.02139 0.0091 1.0000 0.9754
-0.250 0.0230 0.03035 0.02116 -0.0040 1.0000 0.9999
0.000 0.0000 0.03036 0.02118 0.0000 1.0000 1.0000
0.250 -0.0230 0.03035 0.02116 0.0040 0.9999 1.0000
0.500 0.0600 0.03056 0.02138 -0.0091 0.9754 1.0000
0.750 0.1382 0.03056 0.02141 -0.0206 0.9519 1.0000
1.000 0.2042 0.03039 0.02129 -0.0291 0.9258 1.0000
1.250 0.2906 0.02981 0.02080 -0.0403 0.9034 1.0000
1.500 0.3428 0.02934 0.02041 -0.0451 0.8763 1.0000
1.750 0.3983 0.02858 0.01972 -0.0494 0.8513 1.0000
2.000 0.4321 0.02816 0.01933 -0.0499 0.8244 1.0000
2.250 0.4623 0.02771 0.01891 -0.0494 0.7982 1.0000
2.500 0.4886 0.02733 0.01852 -0.0480 0.7732 1.0000
2.750 0.5068 0.02726 0.01845 -0.0456 0.7462 1.0000
3.000 0.5298 0.02694 0.01810 -0.0433 0.7220 1.0000
3.250 0.5462 0.02704 0.01818 -0.0407 0.6957 1.0000
3.500 0.5651 0.02701 0.01810 -0.0381 0.6703 1.0000
3.750 0.5859 0.02691 0.01791 -0.0355 0.6464 1.0000
4.000 0.6009 0.02725 0.01825 -0.0328 0.6194 1.0000
4.250 0.6208 0.02729 0.01819 -0.0303 0.5946 1.0000
4.500 0.6379 0.02760 0.01847 -0.0277 0.5689 1.0000
4.750 0.6556 0.02790 0.01869 -0.0252 0.5431 1.0000
5.000 0.6764 0.02807 0.01870 -0.0229 0.5187 1.0000
5.250 0.6909 0.02869 0.01933 -0.0203 0.4924 1.0000
5.500 0.7102 0.02904 0.01955 -0.0180 0.4678 1.0000
5.750 0.7272 0.02962 0.02006 -0.0157 0.4434 1.0000
6.000 0.7430 0.03031 0.02071 -0.0132 0.4190 1.0000
6.250 0.7621 0.03086 0.02112 -0.0111 0.3959 1.0000
6.500 0.7795 0.03163 0.02178 -0.0089 0.3738 1.0000
6.750 0.7934 0.03263 0.02280 -0.0064 0.3520 1.0000
7.000 0.8088 0.03359 0.02373 -0.0041 0.3315 1.0000
7.250 0.8247 0.03460 0.02470 -0.0019 0.3123 1.0000
7.500 0.8401 0.03572 0.02578 0.0003 0.2944 1.0000
7.750 0.8544 0.03697 0.02703 0.0026 0.2778 1.0000
8.000 0.8680 0.03838 0.02846 0.0048 0.2627 1.0000
8.250 0.8818 0.03986 0.02996 0.0070 0.2489 1.0000
8.500 0.8996 0.04122 0.03121 0.0086 0.2360 1.0000
8.750 0.9077 0.04310 0.03329 0.0112 0.2249 1.0000
9.000 0.9132 0.04547 0.03586 0.0138 0.2160 1.0000
9.250 0.9334 0.04694 0.03723 0.0150 0.2061 1.0000
9.500 0.9249 0.05030 0.04100 0.0185 0.2010 1.0000
9.750 0.9167 0.05358 0.04459 0.0216 0.1959 1.0000
10.000 0.9434 0.05519 0.04600 0.0220 0.1883 1.0000
10.250 0.9177 0.05971 0.05095 0.0256 0.1869 1.0000
10.500 0.8853 0.06478 0.05630 0.0286 0.1865 1.0000
10.750 0.8443 0.07039 0.06208 0.0310 0.1873 1.0000
11.000 0.8024 0.07755 0.06932 0.0307 0.1885 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0015 (naca0015-il)