NACA 66-206 (naca66206-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-206 (naca66206-il) Reynolds number: 50,000 Max Cl/Cd: 20.93 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66206-il-50000.txt Download as CSV file: xf-naca66206-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-206
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5628 0.11708 0.11007 -0.0062 1.0000 0.1656
-9.250 -0.5519 0.11244 0.10545 -0.0055 1.0000 0.1755
-9.000 -0.5673 0.11125 0.10439 -0.0090 1.0000 0.1798
-8.750 -0.5584 0.10695 0.10012 -0.0083 1.0000 0.1926
-8.500 -0.5525 0.10312 0.09634 -0.0080 1.0000 0.2052
-8.250 -0.5509 0.09974 0.09302 -0.0080 1.0000 0.2185
-8.000 -0.5520 0.09666 0.09003 -0.0081 1.0000 0.2323
-7.750 -0.5400 0.09258 0.08597 -0.0060 1.0000 0.2551
-7.500 -0.5369 0.08943 0.08289 -0.0045 1.0000 0.2806
-7.250 -0.5358 0.08664 0.08017 -0.0024 1.0000 0.3106
-7.000 -0.5256 0.08334 0.07692 0.0008 1.0000 0.3481
-6.750 -0.5374 0.08162 0.07534 0.0034 1.0000 0.3807
-6.500 -0.5069 0.07756 0.07122 0.0091 1.0000 0.4463
-6.250 -0.4743 0.07360 0.06711 0.0146 1.0000 0.5261
-6.000 -0.4398 0.07000 0.06345 0.0199 1.0000 0.6219
-5.250 -0.3397 0.05667 0.04999 0.0184 1.0000 0.7747
-5.000 -0.4138 0.05732 0.05102 0.0216 1.0000 0.6554
-4.750 -0.4588 0.05610 0.05010 0.0246 1.0000 0.6119
-4.250 -0.4134 0.03893 0.03016 -0.0310 1.0000 0.1656
-4.000 -0.3846 0.03534 0.02595 -0.0305 1.0000 0.1364
-3.750 -0.3577 0.03241 0.02242 -0.0295 1.0000 0.1207
-3.500 -0.3305 0.03006 0.01941 -0.0283 1.0000 0.1110
-3.250 -0.3052 0.02785 0.01680 -0.0271 1.0000 0.1100
-3.000 -0.2807 0.02584 0.01452 -0.0260 1.0000 0.1169
-2.750 -0.2547 0.02405 0.01248 -0.0246 1.0000 0.1181
-2.500 -0.2289 0.02252 0.01078 -0.0228 1.0000 0.1219
-2.250 -0.2045 0.02120 0.00931 -0.0211 1.0000 0.1293
-2.000 -0.1826 0.01996 0.00805 -0.0196 1.0000 0.1485
-1.750 -0.1226 0.01561 0.00650 -0.0206 1.0000 1.0000
-1.500 -0.1097 0.01555 0.00594 -0.0181 1.0000 1.0000
-1.250 -0.0951 0.01552 0.00554 -0.0160 1.0000 1.0000
-1.000 -0.0787 0.01552 0.00523 -0.0143 1.0000 1.0000
-0.750 -0.0609 0.01555 0.00499 -0.0130 1.0000 1.0000
-0.500 -0.0420 0.01561 0.00483 -0.0118 1.0000 1.0000
-0.250 -0.0223 0.01569 0.00472 -0.0108 1.0000 1.0000
0.000 -0.0021 0.01580 0.00461 -0.0100 1.0000 1.0000
0.250 0.0186 0.01593 0.00461 -0.0092 1.0000 1.0000
0.500 0.0395 0.01608 0.00467 -0.0085 1.0000 1.0000
0.750 0.0606 0.01625 0.00478 -0.0078 1.0000 1.0000
1.000 0.0819 0.01645 0.00494 -0.0073 1.0000 1.0000
1.250 0.1032 0.01667 0.00515 -0.0067 1.0000 1.0000
1.500 0.1246 0.01691 0.00544 -0.0062 1.0000 1.0000
1.750 0.1459 0.01718 0.00575 -0.0057 1.0000 1.0000
2.000 0.1672 0.01748 0.00611 -0.0052 1.0000 1.0000
2.250 0.1884 0.01780 0.00654 -0.0048 1.0000 1.0000
2.500 0.2094 0.01816 0.00703 -0.0044 1.0000 1.0000
2.750 0.2303 0.01855 0.00758 -0.0040 1.0000 1.0000
3.000 0.2510 0.01898 0.00822 -0.0036 1.0000 1.0000
3.250 0.2714 0.01945 0.00903 -0.0032 1.0000 1.0000
3.500 0.2915 0.01997 0.00984 -0.0029 1.0000 1.0000
3.750 0.3114 0.02054 0.01075 -0.0026 1.0000 1.0000
4.000 0.3309 0.02118 0.01181 -0.0023 1.0000 1.0000
4.250 0.5587 0.02669 0.01471 -0.0195 0.1049 1.0000
4.500 0.5931 0.02958 0.01771 -0.0194 0.1025 1.0000
4.750 0.6238 0.03240 0.02091 -0.0187 0.1031 1.0000
5.000 0.6528 0.03486 0.02423 -0.0171 0.1089 1.0000
5.250 0.6795 0.03880 0.02847 -0.0162 0.1154 1.0000
5.500 0.7046 0.04217 0.03266 -0.0146 0.1277 1.0000
5.750 0.7274 0.04599 0.03718 -0.0133 0.1405 1.0000
6.000 0.7507 0.05059 0.04282 -0.0128 0.1761 1.0000
6.250 0.7569 0.06329 0.05740 -0.0346 0.3880 1.0000
6.500 0.7132 0.07093 0.06496 -0.0470 0.4549 1.0000
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Polar data table (+)
Polar graphs
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