NACA 16-006 (naca16006-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16-006 (naca16006-il) Reynolds number: 500,000 Max Cl/Cd: 33.97 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16006-il-500000-n5.txt Download as CSV file: xf-naca16006-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-006
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5102 0.09891 0.09675 -0.0070 1.0000 0.0056
-9.750 -0.5122 0.09468 0.09253 -0.0081 1.0000 0.0057
-5.250 -0.5859 0.03351 0.02968 -0.0010 1.0000 0.0043
-4.750 -0.5420 0.02357 0.01884 0.0034 0.9976 0.0029
-4.500 -0.5165 0.01972 0.01447 0.0042 0.9962 0.0028
-4.250 -0.4892 0.01660 0.01083 0.0050 0.9953 0.0028
-4.000 -0.4622 0.01447 0.00832 0.0057 0.9941 0.0029
-3.750 -0.4360 0.01283 0.00647 0.0060 0.9928 0.0034
-3.500 -0.4074 0.01218 0.00573 0.0057 0.9913 0.0044
-3.250 -0.3790 0.01135 0.00476 0.0055 0.9898 0.0054
-3.000 -0.3505 0.01048 0.00375 0.0052 0.9885 0.0062
-2.750 -0.3202 0.00998 0.00316 0.0045 0.9874 0.0082
-2.500 -0.2925 0.00952 0.00263 0.0045 0.9850 0.0154
-2.250 -0.2634 0.00921 0.00236 0.0040 0.9830 0.0367
-2.000 -0.2346 0.00868 0.00211 0.0033 0.9812 0.1159
-1.750 -0.2079 0.00770 0.00187 0.0027 0.9796 0.3313
-1.500 -0.1812 0.00678 0.00167 0.0023 0.9783 0.5421
-1.250 -0.1627 0.00587 0.00156 0.0041 0.9744 0.7548
-1.000 -0.1373 0.00559 0.00173 0.0051 0.9727 0.8824
-0.750 -0.1066 0.00576 0.00199 0.0051 0.9719 0.9412
-0.500 -0.0712 0.00592 0.00215 0.0036 0.9714 0.9579
-0.250 -0.0363 0.00602 0.00222 0.0021 0.9704 0.9671
0.000 -0.0001 0.00603 0.00223 0.0000 0.9691 0.9691
0.250 0.0361 0.00602 0.00222 -0.0020 0.9670 0.9704
0.500 0.0712 0.00592 0.00214 -0.0036 0.9577 0.9713
0.750 0.1064 0.00576 0.00200 -0.0051 0.9411 0.9719
1.000 0.1372 0.00560 0.00173 -0.0051 0.8826 0.9726
1.250 0.1626 0.00587 0.00156 -0.0041 0.7550 0.9744
1.500 0.1809 0.00678 0.00167 -0.0022 0.5427 0.9782
1.750 0.2075 0.00770 0.00187 -0.0027 0.3318 0.9796
2.000 0.2343 0.00867 0.00211 -0.0033 0.1171 0.9811
2.250 0.2631 0.00921 0.00236 -0.0039 0.0368 0.9829
2.500 0.2922 0.00952 0.00263 -0.0044 0.0154 0.9850
2.750 0.3197 0.00998 0.00316 -0.0044 0.0082 0.9874
3.000 0.3500 0.01047 0.00375 -0.0051 0.0062 0.9884
3.250 0.3783 0.01134 0.00475 -0.0053 0.0054 0.9897
3.500 0.4067 0.01217 0.00571 -0.0055 0.0044 0.9911
3.750 0.4355 0.01282 0.00646 -0.0059 0.0034 0.9926
4.000 0.4618 0.01451 0.00837 -0.0056 0.0029 0.9940
4.250 0.4888 0.01660 0.01084 -0.0049 0.0028 0.9952
4.500 0.5159 0.01968 0.01442 -0.0041 0.0028 0.9961
4.750 0.5414 0.02350 0.01876 -0.0032 0.0029 0.9974
5.750 0.5785 0.02518 0.02215 0.0079 0.0058 1.0000
6.000 0.5831 0.02868 0.02584 0.0109 0.0058 1.0000
6.250 0.5863 0.03228 0.02959 0.0137 0.0058 1.0000
6.500 0.5882 0.03591 0.03336 0.0162 0.0057 1.0000
6.750 0.5885 0.03983 0.03740 0.0184 0.0056 1.0000
7.000 0.5875 0.04386 0.04153 0.0203 0.0056 1.0000
7.250 0.5847 0.04801 0.04578 0.0218 0.0055 1.0000
7.500 0.5802 0.05242 0.05026 0.0226 0.0055 1.0000
7.750 0.5733 0.05689 0.05479 0.0227 0.0055 1.0000
8.000 0.5608 0.06106 0.05900 0.0228 0.0056 1.0000
8.250 0.5446 0.06636 0.06430 0.0189 0.0057 1.0000
8.500 0.5344 0.07160 0.06952 0.0156 0.0057 1.0000
8.750 0.5274 0.07649 0.07440 0.0135 0.0058 1.0000
9.000 0.5221 0.08120 0.07909 0.0118 0.0058 1.0000
9.250 0.5178 0.08577 0.08364 0.0105 0.0058 1.0000
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Polar data table (+)
Polar graphs
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