NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-206 (naca64206-il) Reynolds number: 100,000 Max Cl/Cd: 43.15 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64206-il-100000.txt Download as CSV file: xf-naca64206-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5668 0.09497 0.09024 -0.0117 1.0000 0.0682
-8.000 -0.5718 0.09108 0.08639 -0.0191 1.0000 0.0686
-7.750 -0.5751 0.08752 0.08272 -0.0260 1.0000 0.0690
-7.500 -0.5549 0.08233 0.07765 -0.0144 1.0000 0.0748
-7.250 -0.5513 0.07801 0.07333 -0.0190 1.0000 0.0783
-7.000 -0.5506 0.07397 0.06904 -0.0294 1.0000 0.0819
-6.750 -0.5415 0.06854 0.06376 -0.0278 1.0000 0.0849
-6.500 -0.5305 0.06502 0.06022 -0.0282 1.0000 0.0910
-6.250 -0.4800 0.04888 0.04441 -0.0287 1.0000 0.1039
-6.000 -0.5077 0.05786 0.05241 -0.0357 1.0000 0.1094
-5.750 -0.4943 0.05306 0.04794 -0.0335 1.0000 0.1157
-5.500 -0.4795 0.04956 0.04430 -0.0345 1.0000 0.1297
-5.250 -0.4643 0.04622 0.04076 -0.0356 1.0000 0.1517
-4.250 -0.4172 0.03670 0.03168 -0.0263 1.0000 0.3278
-4.000 -0.4044 0.03470 0.02981 -0.0224 1.0000 0.3735
-3.750 -0.2996 0.02491 0.01625 -0.0350 1.0000 0.0678
-3.500 -0.2739 0.02206 0.01307 -0.0341 1.0000 0.0632
-3.250 -0.2477 0.02006 0.01074 -0.0329 1.0000 0.0609
-3.000 -0.2228 0.01857 0.00910 -0.0319 1.0000 0.0648
-2.750 -0.1984 0.01716 0.00760 -0.0308 1.0000 0.0709
-2.500 -0.1753 0.01578 0.00631 -0.0297 1.0000 0.0758
-2.250 -0.1520 0.01467 0.00519 -0.0286 1.0000 0.0851
-2.000 -0.1278 0.01348 0.00420 -0.0281 1.0000 0.1278
-1.750 -0.1041 0.01034 0.00406 -0.0224 1.0000 1.0000
-1.500 -0.0887 0.01026 0.00370 -0.0209 1.0000 1.0000
-1.250 -0.0683 0.01023 0.00344 -0.0203 1.0000 1.0000
-1.000 -0.0462 0.01026 0.00326 -0.0199 1.0000 1.0000
-0.750 -0.0236 0.01032 0.00316 -0.0196 1.0000 1.0000
-0.500 -0.0008 0.01042 0.00311 -0.0192 1.0000 1.0000
-0.250 0.0218 0.01055 0.00310 -0.0189 1.0000 1.0000
0.000 0.0442 0.01071 0.00316 -0.0187 1.0000 1.0000
0.250 0.0664 0.01090 0.00328 -0.0184 1.0000 1.0000
0.500 0.0883 0.01113 0.00346 -0.0181 1.0000 1.0000
0.750 0.1099 0.01139 0.00370 -0.0178 1.0000 1.0000
1.000 0.1311 0.01169 0.00400 -0.0176 1.0000 1.0000
1.250 0.1520 0.01204 0.00436 -0.0174 1.0000 1.0000
1.500 0.1726 0.01243 0.00477 -0.0172 1.0000 1.0000
1.750 0.2183 0.01294 0.00538 -0.0219 0.9892 1.0000
2.000 0.2653 0.01343 0.00601 -0.0266 0.9784 1.0000
2.250 0.3142 0.01386 0.00663 -0.0315 0.9663 1.0000
2.500 0.3637 0.01415 0.00725 -0.0362 0.9518 1.0000
2.750 0.4715 0.01196 0.00565 -0.0446 0.8679 1.0000
3.000 0.4902 0.01136 0.00495 -0.0382 0.7541 1.0000
3.250 0.4856 0.01512 0.00528 -0.0304 0.1118 1.0000
3.500 0.5072 0.01674 0.00685 -0.0291 0.0841 1.0000
3.750 0.5295 0.01832 0.00835 -0.0280 0.0716 1.0000
4.000 0.5551 0.01961 0.00970 -0.0271 0.0625 1.0000
4.250 0.5815 0.02189 0.01190 -0.0265 0.0593 1.0000
4.500 0.6099 0.02453 0.01468 -0.0258 0.0588 1.0000
4.750 0.6392 0.02644 0.01701 -0.0247 0.0607 1.0000
5.000 0.6448 0.01667 0.00807 -0.0219 0.0591 1.0000
5.250 0.6708 0.01929 0.01162 -0.0200 0.0665 1.0000
9.000 0.7228 0.09871 0.09467 -0.0276 0.0970 1.0000
9.250 0.7052 0.10448 0.10040 -0.0328 0.0966 1.0000
9.500 0.6893 0.10973 0.10560 -0.0375 0.0952 1.0000
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Polar data table (+)
Polar graphs
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