NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.81 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64208-il-1000000.txt Download as CSV file: xf-naca64208-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-208
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4791 0.09407 0.09254 -0.0105 1.0000 0.0088
-10.000 -0.4811 0.08900 0.08747 -0.0124 1.0000 0.0088
-9.750 -0.4837 0.08385 0.08233 -0.0143 1.0000 0.0089
-9.500 -0.4856 0.07912 0.07762 -0.0162 1.0000 0.0090
-9.250 -0.4888 0.07423 0.07274 -0.0181 1.0000 0.0091
-9.000 -0.4940 0.06886 0.06738 -0.0205 1.0000 0.0092
-8.750 -0.5041 0.06232 0.06086 -0.0241 1.0000 0.0091
-8.500 -0.5291 0.05262 0.05116 -0.0329 1.0000 0.0090
-6.750 -0.5716 0.02831 0.02530 -0.0367 1.0000 0.0076
-6.500 -0.5614 0.02236 0.01880 -0.0343 1.0000 0.0081
-6.250 -0.5381 0.02029 0.01643 -0.0339 0.9991 0.0084
-6.000 -0.5090 0.01518 0.01064 -0.0353 0.9960 0.0088
-5.750 -0.4772 0.01340 0.00867 -0.0368 0.9932 0.0095
-5.500 -0.4442 0.01325 0.00851 -0.0382 0.9895 0.0104
-5.250 -0.4108 0.01237 0.00753 -0.0396 0.9861 0.0114
-5.000 -0.3765 0.01153 0.00658 -0.0411 0.9829 0.0123
-4.750 -0.3452 0.01094 0.00592 -0.0420 0.9760 0.0129
-4.500 -0.3126 0.01010 0.00499 -0.0432 0.9697 0.0134
-4.250 -0.2845 0.00889 0.00368 -0.0436 0.9593 0.0154
-4.000 -0.2559 0.00859 0.00335 -0.0438 0.9484 0.0170
-3.750 -0.2289 0.00826 0.00294 -0.0436 0.9366 0.0183
-3.500 -0.2023 0.00801 0.00261 -0.0433 0.9248 0.0194
-3.000 -0.1493 0.00738 0.00183 -0.0427 0.9020 0.0271
-2.750 -0.1223 0.00720 0.00158 -0.0425 0.8909 0.0328
-2.500 -0.0953 0.00697 0.00137 -0.0423 0.8801 0.0494
-2.250 -0.0689 0.00644 0.00116 -0.0424 0.8696 0.1527
-2.000 -0.0438 0.00531 0.00090 -0.0427 0.8590 0.4233
-1.750 -0.0172 0.00489 0.00083 -0.0427 0.8483 0.5460
-1.500 0.0101 0.00473 0.00080 -0.0426 0.8379 0.6004
-1.250 0.0376 0.00467 0.00076 -0.0425 0.8275 0.6309
-1.000 0.0649 0.00458 0.00076 -0.0424 0.8170 0.6718
-0.750 0.0922 0.00450 0.00077 -0.0422 0.8067 0.7116
-0.500 0.1196 0.00447 0.00078 -0.0421 0.7964 0.7395
-0.250 0.1470 0.00447 0.00079 -0.0419 0.7859 0.7627
0.000 0.1747 0.00447 0.00080 -0.0418 0.7752 0.7759
0.250 0.2025 0.00448 0.00081 -0.0418 0.7640 0.7875
0.500 0.2301 0.00449 0.00083 -0.0417 0.7517 0.7991
0.750 0.2576 0.00452 0.00085 -0.0416 0.7380 0.8106
1.000 0.2847 0.00458 0.00086 -0.0413 0.7162 0.8221
1.250 0.3115 0.00467 0.00089 -0.0411 0.6888 0.8336
1.500 0.3379 0.00479 0.00092 -0.0407 0.6518 0.8456
1.750 0.3646 0.00488 0.00098 -0.0405 0.6247 0.8575
2.000 0.3912 0.00498 0.00104 -0.0402 0.5979 0.8694
2.250 0.4170 0.00516 0.00112 -0.0398 0.5559 0.8816
2.500 0.4417 0.00548 0.00124 -0.0392 0.4859 0.8943
2.750 0.4634 0.00626 0.00148 -0.0383 0.3372 0.9085
3.000 0.4832 0.00733 0.00187 -0.0373 0.1554 0.9243
3.250 0.5045 0.00802 0.00218 -0.0362 0.0553 0.9416
3.500 0.5284 0.00829 0.00240 -0.0354 0.0337 0.9625
4.000 0.5885 0.00890 0.00305 -0.0366 0.0216 1.0000
4.250 0.6159 0.00919 0.00336 -0.0366 0.0191 1.0000
4.500 0.6422 0.00967 0.00387 -0.0365 0.0162 1.0000
4.750 0.6670 0.01046 0.00477 -0.0360 0.0149 1.0000
5.000 0.6932 0.01090 0.00525 -0.0358 0.0144 1.0000
5.250 0.7189 0.01143 0.00584 -0.0355 0.0138 1.0000
5.500 0.7443 0.01203 0.00649 -0.0352 0.0131 1.0000
5.750 0.7700 0.01254 0.00705 -0.0350 0.0122 1.0000
6.000 0.7962 0.01292 0.00744 -0.0349 0.0113 1.0000
6.250 0.8200 0.01385 0.00843 -0.0344 0.0104 1.0000
6.750 0.8642 0.01748 0.01241 -0.0326 0.0094 1.0000
7.000 0.8890 0.01836 0.01341 -0.0322 0.0090 1.0000
7.250 0.9131 0.01950 0.01471 -0.0317 0.0085 1.0000
7.500 0.9371 0.02039 0.01573 -0.0313 0.0078 1.0000
7.750 0.9611 0.02103 0.01645 -0.0310 0.0073 1.0000
8.000 0.9849 0.02153 0.01702 -0.0307 0.0069 1.0000
8.250 1.0062 0.02282 0.01844 -0.0301 0.0066 1.0000
8.500 1.0200 0.02620 0.02220 -0.0286 0.0063 1.0000
8.750 1.0171 0.03328 0.03000 -0.0255 0.0061 1.0000
9.000 1.0060 0.04076 0.03808 -0.0223 0.0061 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64-208 (naca64208-il)