NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-206 (naca64206-il) Reynolds number: 100,000 Max Cl/Cd: 40.99 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64206-il-100000-n5.txt Download as CSV file: xf-naca64206-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4657 0.08923 0.08459 -0.0085 1.0000 0.0363
-8.500 -0.4655 0.08508 0.08047 -0.0097 1.0000 0.0368
-8.250 -0.4657 0.08086 0.07628 -0.0111 1.0000 0.0373
-8.000 -0.4671 0.07655 0.07201 -0.0127 1.0000 0.0378
-7.750 -0.4692 0.07234 0.06784 -0.0146 1.0000 0.0379
-7.500 -0.4733 0.06797 0.06353 -0.0167 1.0000 0.0381
-7.250 -0.4787 0.06355 0.05915 -0.0198 1.0000 0.0379
-7.000 -0.4805 0.05834 0.05393 -0.0240 1.0000 0.0379
-6.750 -0.4777 0.05269 0.04816 -0.0276 1.0000 0.0303
-6.500 -0.4739 0.04739 0.04280 -0.0295 1.0000 0.0271
-6.250 -0.4678 0.04158 0.03682 -0.0320 1.0000 0.0244
-5.750 -0.4674 0.04647 0.04060 -0.0352 1.0000 0.0194
-5.500 -0.4505 0.04220 0.03604 -0.0358 1.0000 0.0189
-5.250 -0.4311 0.03827 0.03176 -0.0361 1.0000 0.0187
-5.000 -0.4099 0.03458 0.02766 -0.0360 1.0000 0.0185
-4.750 -0.3871 0.03137 0.02400 -0.0357 1.0000 0.0188
-4.500 -0.3630 0.02856 0.02062 -0.0352 1.0000 0.0211
-4.250 -0.3408 0.02577 0.01753 -0.0350 1.0000 0.0233
-4.000 -0.3160 0.02335 0.01471 -0.0342 1.0000 0.0241
-3.750 -0.2911 0.02129 0.01232 -0.0333 1.0000 0.0252
-3.500 -0.2664 0.01952 0.01029 -0.0323 1.0000 0.0270
-3.250 -0.2418 0.01867 0.00917 -0.0315 1.0000 0.0329
-3.000 -0.2187 0.01690 0.00730 -0.0305 1.0000 0.0351
-2.750 -0.1958 0.01576 0.00612 -0.0296 1.0000 0.0379
-2.500 -0.1722 0.01494 0.00517 -0.0289 1.0000 0.0427
-2.250 -0.1483 0.01421 0.00434 -0.0283 1.0000 0.0525
-2.000 -0.1241 0.01326 0.00365 -0.0280 1.0000 0.1094
-1.750 -0.1133 0.01075 0.00371 -0.0247 1.0000 0.7288
-1.500 -0.1097 0.01042 0.00382 -0.0177 1.0000 0.8957
-1.250 -0.0666 0.01022 0.00337 -0.0205 1.0000 1.0000
-1.000 -0.0443 0.01025 0.00320 -0.0202 1.0000 1.0000
-0.750 -0.0181 0.01032 0.00309 -0.0206 0.9982 1.0000
-0.500 0.0211 0.01043 0.00304 -0.0235 0.9894 1.0000
-0.250 0.0597 0.01053 0.00300 -0.0262 0.9807 1.0000
0.000 0.0979 0.01062 0.00300 -0.0288 0.9717 1.0000
0.250 0.1363 0.01071 0.00305 -0.0313 0.9632 1.0000
0.500 0.1756 0.01080 0.00312 -0.0340 0.9551 1.0000
0.750 0.2112 0.01088 0.00323 -0.0358 0.9447 1.0000
1.000 0.2467 0.01096 0.00335 -0.0376 0.9345 1.0000
1.250 0.2820 0.01104 0.00350 -0.0393 0.9242 1.0000
1.500 0.3167 0.01112 0.00368 -0.0407 0.9137 1.0000
1.750 0.3501 0.01121 0.00395 -0.0419 0.9022 1.0000
2.000 0.3817 0.01131 0.00420 -0.0426 0.8895 1.0000
2.250 0.4131 0.01140 0.00445 -0.0431 0.8751 1.0000
2.500 0.4404 0.01132 0.00450 -0.0418 0.8389 1.0000
2.750 0.4583 0.01118 0.00396 -0.0368 0.7092 1.0000
3.000 0.4750 0.01194 0.00393 -0.0333 0.5000 1.0000
3.250 0.4849 0.01502 0.00475 -0.0312 0.0760 1.0000
3.500 0.5087 0.01604 0.00573 -0.0305 0.0520 1.0000
3.750 0.5329 0.01700 0.00686 -0.0298 0.0448 1.0000
4.000 0.5561 0.01813 0.00812 -0.0289 0.0404 1.0000
4.250 0.5794 0.01933 0.00941 -0.0282 0.0330 1.0000
4.500 0.6037 0.02082 0.01102 -0.0274 0.0295 1.0000
4.750 0.6288 0.02271 0.01313 -0.0266 0.0272 1.0000
5.000 0.6542 0.02546 0.01606 -0.0260 0.0255 1.0000
5.250 0.6801 0.02752 0.01858 -0.0251 0.0221 1.0000
5.500 0.7052 0.03017 0.02174 -0.0241 0.0201 1.0000
5.750 0.7283 0.03349 0.02561 -0.0230 0.0194 1.0000
6.000 0.7492 0.03720 0.02988 -0.0218 0.0191 1.0000
6.250 0.7677 0.04128 0.03448 -0.0206 0.0191 1.0000
6.500 0.7836 0.04565 0.03933 -0.0196 0.0193 1.0000
6.750 0.7972 0.05007 0.04417 -0.0188 0.0190 1.0000
7.000 0.8085 0.05424 0.04869 -0.0184 0.0176 1.0000
7.250 0.8173 0.05844 0.05318 -0.0183 0.0168 1.0000
7.500 0.8235 0.06233 0.05728 -0.0184 0.0157 1.0000
7.750 0.8261 0.06695 0.06212 -0.0188 0.0155 1.0000
8.000 0.8244 0.07208 0.06743 -0.0197 0.0156 1.0000
8.250 0.8183 0.07761 0.07310 -0.0215 0.0161 1.0000
8.500 0.8074 0.08294 0.07851 -0.0239 0.0168 1.0000
8.750 0.7973 0.08913 0.08472 -0.0289 0.0173 1.0000
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Polar data table (+)
Polar graphs
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