NACA 64-008A AIRFOIL (n64008a-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-008A AIRFOIL (n64008a-il) Reynolds number: 200,000 Max Cl/Cd: 40.96 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n64008a-il-200000.txt Download as CSV file: xf-n64008a-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-008A AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5467 0.10892 0.10559 0.0049 1.0000 0.0408
-10.250 -0.5494 0.10455 0.10123 0.0035 1.0000 0.0420
-10.000 -0.6908 0.10447 0.10108 0.0065 1.0000 0.0364
-9.750 -0.6867 0.10132 0.09792 0.0079 1.0000 0.0374
-9.500 -0.6847 0.09747 0.09408 0.0070 1.0000 0.0383
-9.250 -0.6852 0.09290 0.08954 0.0046 1.0000 0.0392
-9.000 -0.6881 0.08752 0.08419 0.0006 1.0000 0.0399
-8.750 -0.6969 0.08065 0.07733 -0.0067 1.0000 0.0399
-8.500 -0.7067 0.07543 0.07206 -0.0104 1.0000 0.0402
-8.250 -0.7110 0.07065 0.06718 -0.0126 1.0000 0.0411
-8.000 -0.7122 0.06602 0.06241 -0.0142 1.0000 0.0425
-7.750 -0.7105 0.06147 0.05764 -0.0153 1.0000 0.0447
-7.500 -0.7066 0.06051 0.05593 -0.0148 1.0000 0.0477
-7.250 -0.6577 0.03969 0.03564 -0.0186 1.0000 0.0506
-7.000 -0.6478 0.03613 0.03201 -0.0179 1.0000 0.0531
-5.250 -0.5595 0.02433 0.01671 -0.0050 1.0000 0.0358
-5.000 -0.5363 0.02145 0.01354 -0.0040 1.0000 0.0363
-4.750 -0.5130 0.01921 0.01123 -0.0032 1.0000 0.0388
-4.500 -0.4885 0.01762 0.00950 -0.0022 1.0000 0.0392
-4.250 -0.4651 0.01632 0.00815 -0.0011 1.0000 0.0406
-4.000 -0.4427 0.01524 0.00704 0.0000 1.0000 0.0431
-3.750 -0.4203 0.01444 0.00617 0.0012 1.0000 0.0469
-3.500 -0.4002 0.01336 0.00513 0.0025 1.0000 0.0537
-3.250 -0.3788 0.01252 0.00426 0.0037 1.0000 0.0644
-3.000 -0.3650 0.01005 0.00316 0.0052 1.0000 0.3378
-2.750 -0.3535 0.00863 0.00319 0.0084 1.0000 0.6690
-2.500 -0.3338 0.00845 0.00324 0.0106 1.0000 0.7481
-2.250 -0.3133 0.00838 0.00326 0.0127 1.0000 0.7952
-2.000 -0.2948 0.00838 0.00336 0.0153 1.0000 0.8404
-1.750 -0.2810 0.00850 0.00359 0.0194 1.0000 0.8885
-1.500 -0.2626 0.00865 0.00376 0.0223 1.0000 0.9250
-1.250 -0.2309 0.00874 0.00378 0.0216 1.0000 0.9447
-1.000 -0.1916 0.00881 0.00376 0.0190 1.0000 0.9595
-0.750 -0.1478 0.00888 0.00376 0.0152 1.0000 0.9720
-0.500 -0.1015 0.00894 0.00377 0.0108 1.0000 0.9829
-0.250 -0.0520 0.00897 0.00376 0.0057 1.0000 0.9907
0.000 0.0000 0.00898 0.00377 0.0000 0.9969 0.9969
0.250 0.0520 0.00897 0.00376 -0.0057 0.9908 1.0000
0.500 0.1014 0.00893 0.00377 -0.0108 0.9829 1.0000
0.750 0.1477 0.00888 0.00376 -0.0152 0.9720 1.0000
1.000 0.1916 0.00881 0.00376 -0.0190 0.9595 1.0000
1.250 0.2308 0.00874 0.00378 -0.0216 0.9447 1.0000
1.500 0.2626 0.00865 0.00376 -0.0223 0.9251 1.0000
1.750 0.2810 0.00850 0.00359 -0.0194 0.8885 1.0000
2.000 0.2948 0.00838 0.00336 -0.0153 0.8404 1.0000
2.250 0.3133 0.00838 0.00326 -0.0127 0.7951 1.0000
2.500 0.3338 0.00845 0.00324 -0.0106 0.7482 1.0000
2.750 0.3535 0.00863 0.00319 -0.0084 0.6690 1.0000
3.000 0.3650 0.01005 0.00316 -0.0052 0.3378 1.0000
3.250 0.3787 0.01252 0.00426 -0.0037 0.0644 1.0000
3.500 0.4001 0.01336 0.00513 -0.0025 0.0537 1.0000
3.750 0.4202 0.01444 0.00616 -0.0012 0.0469 1.0000
4.000 0.4425 0.01524 0.00704 0.0000 0.0431 1.0000
4.250 0.4650 0.01631 0.00815 0.0012 0.0406 1.0000
4.500 0.4884 0.01761 0.00950 0.0022 0.0392 1.0000
4.750 0.5129 0.01921 0.01122 0.0033 0.0388 1.0000
5.000 0.5361 0.02143 0.01352 0.0040 0.0363 1.0000
5.250 0.5593 0.02432 0.01670 0.0050 0.0358 1.0000
5.500 0.5960 0.03178 0.02580 0.0102 0.0967 1.0000
5.750 0.6167 0.03414 0.02825 0.0110 0.0897 1.0000
6.000 0.6335 0.03638 0.03086 0.0121 0.0781 1.0000
6.250 0.6485 0.03947 0.03425 0.0130 0.0694 1.0000
6.500 0.6667 0.04192 0.03663 0.0133 0.0627 1.0000
6.750 0.6776 0.04532 0.04061 0.0146 0.0548 1.0000
7.000 0.6918 0.04833 0.04377 0.0151 0.0513 1.0000
7.250 0.7057 0.05194 0.04734 0.0153 0.0493 1.0000
8.250 0.6411 0.06017 0.05682 0.0191 0.0459 1.0000
8.500 0.6232 0.06483 0.06158 0.0182 0.0457 1.0000
8.750 0.6059 0.07008 0.06688 0.0157 0.0459 1.0000
9.000 0.5906 0.07636 0.07317 0.0115 0.0462 1.0000
9.250 0.5778 0.08305 0.07984 0.0069 0.0461 1.0000
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Polar data table (+)
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