NACA 16-006 (naca16006-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 16-006 (naca16006-il) Reynolds number: 50,000 Max Cl/Cd: 16.36 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca16006-il-50000.txt Download as CSV file: xf-naca16006-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6510 0.09973 0.09304 0.0113 1.0000 0.2722
-8.000 -0.6434 0.09584 0.08919 0.0133 1.0000 0.2952
-7.750 -0.6589 0.09338 0.08685 0.0131 1.0000 0.3141
-7.500 -0.6347 0.08949 0.08292 0.0190 1.0000 0.3646
-7.250 -0.6193 0.08613 0.07956 0.0239 1.0000 0.4160
-7.000 -0.6228 0.08394 0.07745 0.0282 1.0000 0.4617
-6.750 -0.5911 0.07993 0.07338 0.0335 1.0000 0.5275
-5.750 -0.5447 0.06505 0.05848 0.0390 1.0000 0.6270
-5.500 -0.5954 0.06222 0.05606 0.0376 1.0000 0.5706
-5.250 -0.6345 0.05328 0.04694 0.0121 1.0000 0.4005
-5.000 -0.5820 0.04360 0.03490 -0.0063 1.0000 0.1626
-4.750 -0.5571 0.03960 0.03009 -0.0049 1.0000 0.1321
-4.500 -0.5321 0.03700 0.02640 -0.0025 1.0000 0.1144
-4.250 -0.5083 0.03335 0.02257 -0.0013 1.0000 0.1093
-4.000 -0.4821 0.03058 0.01923 0.0003 1.0000 0.1047
-3.750 -0.4542 0.02811 0.01616 0.0016 1.0000 0.1043
-3.500 -0.4275 0.02613 0.01393 0.0025 1.0000 0.1163
-3.250 -0.2305 0.01783 0.00851 -0.0213 1.0000 1.0000
-3.000 -0.2111 0.01755 0.00766 -0.0199 1.0000 1.0000
-2.750 -0.1924 0.01729 0.00700 -0.0186 1.0000 1.0000
-2.500 -0.1739 0.01706 0.00635 -0.0172 1.0000 1.0000
-2.250 -0.1557 0.01686 0.00589 -0.0157 1.0000 1.0000
-2.000 -0.1377 0.01670 0.00550 -0.0142 1.0000 1.0000
-1.750 -0.1199 0.01655 0.00517 -0.0126 1.0000 1.0000
-1.500 -0.1025 0.01643 0.00490 -0.0109 1.0000 1.0000
-1.250 -0.0852 0.01633 0.00468 -0.0091 1.0000 1.0000
-1.000 -0.0681 0.01625 0.00451 -0.0073 1.0000 1.0000
-0.750 -0.0510 0.01619 0.00434 -0.0055 1.0000 1.0000
-0.500 -0.0340 0.01614 0.00424 -0.0037 1.0000 1.0000
-0.250 -0.0170 0.01612 0.00418 -0.0018 1.0000 1.0000
0.000 0.0000 0.01611 0.00415 0.0000 1.0000 1.0000
0.250 0.0170 0.01612 0.00418 0.0018 1.0000 1.0000
0.500 0.0340 0.01614 0.00424 0.0037 1.0000 1.0000
0.750 0.0510 0.01619 0.00434 0.0055 1.0000 1.0000
1.000 0.0681 0.01625 0.00451 0.0073 1.0000 1.0000
1.250 0.0852 0.01633 0.00468 0.0091 1.0000 1.0000
1.500 0.1025 0.01643 0.00490 0.0109 1.0000 1.0000
1.750 0.1200 0.01655 0.00517 0.0125 1.0000 1.0000
2.000 0.1377 0.01669 0.00550 0.0142 1.0000 1.0000
2.250 0.1557 0.01686 0.00588 0.0157 1.0000 1.0000
2.500 0.1740 0.01706 0.00634 0.0171 1.0000 1.0000
2.750 0.1925 0.01728 0.00700 0.0185 1.0000 1.0000
3.000 0.2113 0.01754 0.00765 0.0199 1.0000 1.0000
3.250 0.2307 0.01782 0.00851 0.0213 1.0000 1.0000
3.500 0.4272 0.02612 0.01392 -0.0025 0.1164 1.0000
3.750 0.4539 0.02810 0.01615 -0.0015 0.1043 1.0000
4.000 0.4817 0.03056 0.01921 -0.0002 0.1047 1.0000
4.250 0.5080 0.03333 0.02255 0.0014 0.1092 1.0000
4.500 0.5318 0.03697 0.02637 0.0026 0.1144 1.0000
4.750 0.5569 0.03959 0.03006 0.0050 0.1320 1.0000
5.000 0.5818 0.04358 0.03488 0.0064 0.1625 1.0000
5.250 0.6345 0.05328 0.04694 -0.0121 0.4006 1.0000
5.500 0.5953 0.06222 0.05605 -0.0376 0.5707 1.0000
5.750 0.5423 0.06560 0.05903 -0.0411 0.6500 1.0000
6.750 0.5903 0.07984 0.07329 -0.0335 0.5271 1.0000
7.000 0.6225 0.08390 0.07741 -0.0283 0.4616 1.0000
7.250 0.6202 0.08614 0.07958 -0.0240 0.4152 1.0000
7.500 0.6492 0.09005 0.08354 -0.0174 0.3539 1.0000
7.750 0.6528 0.09292 0.08637 -0.0140 0.3165 1.0000
8.000 0.6443 0.09587 0.08921 -0.0134 0.2944 1.0000
8.250 0.6510 0.09973 0.09303 -0.0116 0.2720 1.0000
8.500 0.6716 0.10461 0.09794 -0.0080 0.2477 1.0000
8.750 0.6507 0.10658 0.09978 -0.0108 0.2383 1.0000
9.000 0.6549 0.11045 0.10361 -0.0103 0.2236 1.0000
9.250 0.6727 0.11598 0.10915 -0.0077 0.2077 1.0000
9.500 0.6506 0.11755 0.11058 -0.0118 0.2028 1.0000
9.750 0.6566 0.12180 0.11481 -0.0115 0.1923 1.0000
10.000 0.6675 0.12667 0.11967 -0.0104 0.1805 1.0000
10.250 0.6540 0.12855 0.12145 -0.0136 0.1746 1.0000
10.500 0.6634 0.13343 0.12643 -0.0130 0.1663 1.0000
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Polar data table (+)
Polar graphs
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