NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-206 (naca64206-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.75 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64206-il-1000000.txt Download as CSV file: xf-naca64206-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-206
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5409 0.08484 0.08325 -0.0098 1.0000 0.0049
-8.000 -0.5408 0.08082 0.07925 -0.0121 1.0000 0.0049
-7.750 -0.5443 0.07658 0.07504 -0.0150 1.0000 0.0049
-7.500 -0.5409 0.07126 0.06971 -0.0216 1.0000 0.0049
-7.250 -0.5348 0.06609 0.06451 -0.0261 1.0000 0.0049
-7.000 -0.5270 0.06091 0.05926 -0.0295 1.0000 0.0049
-6.750 -0.5305 0.05132 0.04949 -0.0342 1.0000 0.0052
-6.500 -0.5193 0.04655 0.04458 -0.0357 1.0000 0.0054
-6.250 -0.5049 0.04341 0.04132 -0.0365 1.0000 0.0057
-6.000 -0.4885 0.03999 0.03775 -0.0369 1.0000 0.0059
-5.750 -0.4704 0.03742 0.03503 -0.0370 1.0000 0.0070
-4.000 -0.2983 0.01470 0.01034 -0.0358 0.9958 0.0087
-3.750 -0.2645 0.01137 0.00663 -0.0367 0.9940 0.0081
-3.500 -0.2323 0.01003 0.00514 -0.0375 0.9909 0.0090
-3.250 -0.1996 0.00874 0.00369 -0.0387 0.9876 0.0106
-3.000 -0.1654 0.00793 0.00281 -0.0402 0.9846 0.0124
-2.750 -0.1304 0.00751 0.00236 -0.0419 0.9817 0.0148
-2.500 -0.0994 0.00719 0.00199 -0.0426 0.9745 0.0173
-2.250 -0.0660 0.00689 0.00164 -0.0439 0.9688 0.0186
-2.000 -0.0359 0.00648 0.00114 -0.0443 0.9592 0.0283
-1.750 -0.0072 0.00581 0.00090 -0.0448 0.9486 0.1685
-1.500 0.0187 0.00467 0.00072 -0.0452 0.9366 0.4801
-1.250 0.0449 0.00430 0.00067 -0.0450 0.9240 0.5973
-1.000 0.0707 0.00403 0.00067 -0.0445 0.9113 0.6947
-0.750 0.0966 0.00390 0.00067 -0.0440 0.8988 0.7552
-0.500 0.1221 0.00380 0.00069 -0.0434 0.8860 0.8045
-0.250 0.1478 0.00376 0.00070 -0.0427 0.8731 0.8383
0.000 0.1731 0.00373 0.00072 -0.0420 0.8598 0.8671
0.250 0.1990 0.00374 0.00073 -0.0414 0.8446 0.8846
0.500 0.2246 0.00376 0.00074 -0.0408 0.8269 0.9004
0.750 0.2497 0.00381 0.00075 -0.0400 0.8063 0.9164
1.000 0.2735 0.00388 0.00074 -0.0389 0.7710 0.9328
1.250 0.2967 0.00400 0.00073 -0.0377 0.7256 0.9516
1.500 0.3237 0.00413 0.00073 -0.0375 0.6779 0.9732
1.750 0.3553 0.00440 0.00078 -0.0384 0.6091 1.0000
2.000 0.3815 0.00475 0.00087 -0.0383 0.5355 1.0000
2.250 0.4036 0.00594 0.00114 -0.0379 0.2945 1.0000
2.500 0.4269 0.00711 0.00150 -0.0377 0.0848 1.0000
2.750 0.4533 0.00764 0.00180 -0.0376 0.0264 1.0000
3.000 0.4807 0.00797 0.00217 -0.0375 0.0193 1.0000
3.250 0.5079 0.00832 0.00257 -0.0374 0.0159 1.0000
3.500 0.5345 0.00883 0.00314 -0.0372 0.0135 1.0000
3.750 0.5594 0.00980 0.00425 -0.0367 0.0123 1.0000
4.000 0.5845 0.01070 0.00524 -0.0362 0.0114 1.0000
4.250 0.6114 0.01110 0.00568 -0.0360 0.0102 1.0000
4.500 0.6376 0.01169 0.00632 -0.0358 0.0089 1.0000
4.750 0.6634 0.01250 0.00723 -0.0354 0.0081 1.0000
5.000 0.6891 0.01345 0.00827 -0.0350 0.0075 1.0000
5.250 0.7145 0.01429 0.00917 -0.0348 0.0066 1.0000
5.500 0.7375 0.01734 0.01260 -0.0337 0.0054 1.0000
5.750 0.7606 0.02082 0.01649 -0.0323 0.0051 1.0000
8.750 0.8051 0.08366 0.08223 -0.0297 0.0059 1.0000
9.000 0.7973 0.09106 0.08962 -0.0369 0.0059 1.0000
9.250 0.7947 0.09694 0.09548 -0.0410 0.0059 1.0000
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Polar data table (+)
Polar graphs
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