NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-206 (naca65206-il) Reynolds number: 100,000 Max Cl/Cd: 40.22 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65206-il-100000.txt Download as CSV file: xf-naca65206-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-206
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5478 0.08948 0.08466 -0.0128 1.0000 0.0662
-7.750 -0.5505 0.08587 0.08113 -0.0159 1.0000 0.0682
-7.500 -0.5514 0.08161 0.07687 -0.0230 1.0000 0.0701
-7.250 -0.5523 0.07840 0.07345 -0.0307 1.0000 0.0713
-7.000 -0.5433 0.07248 0.06771 -0.0283 1.0000 0.0740
-6.750 -0.5341 0.06894 0.06417 -0.0281 1.0000 0.0788
-6.250 -0.5167 0.06061 0.05565 -0.0327 1.0000 0.0892
-6.000 -0.5050 0.05724 0.05189 -0.0359 1.0000 0.0992
-5.750 -0.4919 0.05342 0.04823 -0.0346 1.0000 0.1072
-5.500 -0.4771 0.05073 0.04518 -0.0361 1.0000 0.1240
-5.250 -0.4642 0.04688 0.04125 -0.0362 1.0000 0.1397
-5.000 -0.4503 0.04354 0.03801 -0.0351 1.0000 0.1570
-4.750 -0.4364 0.04091 0.03535 -0.0343 1.0000 0.1876
-3.750 -0.3192 0.02742 0.01925 -0.0338 1.0000 0.0970
-3.500 -0.2891 0.02490 0.01600 -0.0319 1.0000 0.0712
-3.250 -0.2646 0.02183 0.01278 -0.0309 1.0000 0.0659
-3.000 -0.2391 0.01993 0.01054 -0.0296 1.0000 0.0625
-2.750 -0.2148 0.01840 0.00887 -0.0283 1.0000 0.0637
-2.500 -0.1912 0.01746 0.00778 -0.0272 1.0000 0.0721
-2.250 -0.1689 0.01590 0.00636 -0.0260 1.0000 0.0760
-2.000 -0.1464 0.01497 0.00540 -0.0249 1.0000 0.0834
-1.750 -0.1230 0.01403 0.00441 -0.0241 1.0000 0.1025
-1.500 -0.1001 0.01066 0.00423 -0.0193 1.0000 1.0000
-1.250 -0.0823 0.01066 0.00390 -0.0180 1.0000 1.0000
-1.000 -0.0621 0.01069 0.00369 -0.0173 1.0000 1.0000
-0.750 -0.0409 0.01077 0.00357 -0.0167 1.0000 1.0000
-0.500 -0.0192 0.01088 0.00352 -0.0162 1.0000 1.0000
-0.250 0.0027 0.01101 0.00349 -0.0158 1.0000 1.0000
0.000 0.0245 0.01118 0.00355 -0.0154 1.0000 1.0000
0.250 0.0463 0.01137 0.00366 -0.0150 1.0000 1.0000
0.500 0.0680 0.01160 0.00382 -0.0147 1.0000 1.0000
0.750 0.0895 0.01185 0.00404 -0.0144 1.0000 1.0000
1.000 0.1108 0.01214 0.00430 -0.0140 1.0000 1.0000
1.250 0.1320 0.01245 0.00462 -0.0138 1.0000 1.0000
1.500 0.1530 0.01280 0.00500 -0.0135 1.0000 1.0000
1.750 0.1737 0.01318 0.00542 -0.0133 1.0000 1.0000
2.000 0.2124 0.01373 0.00607 -0.0166 0.9930 1.0000
2.250 0.2575 0.01430 0.00679 -0.0209 0.9831 1.0000
2.500 0.3021 0.01479 0.00749 -0.0251 0.9717 1.0000
2.750 0.4625 0.01150 0.00511 -0.0401 0.8195 1.0000
3.000 0.4558 0.01470 0.00481 -0.0303 0.1171 1.0000
3.250 0.4769 0.01619 0.00615 -0.0288 0.0868 1.0000
3.500 0.4982 0.01762 0.00752 -0.0275 0.0741 1.0000
3.750 0.5225 0.01884 0.00885 -0.0266 0.0645 1.0000
4.000 0.5482 0.02129 0.01116 -0.0259 0.0613 1.0000
4.250 0.5769 0.02347 0.01349 -0.0252 0.0609 1.0000
4.500 0.6060 0.02551 0.01582 -0.0244 0.0623 1.0000
4.750 0.6324 0.02805 0.01879 -0.0234 0.0597 1.0000
5.000 0.6587 0.03165 0.02264 -0.0227 0.0617 1.0000
5.250 0.6898 0.03625 0.02800 -0.0206 0.0871 1.0000
6.500 0.7938 0.05675 0.05166 -0.0162 0.1461 1.0000
7.750 0.8258 0.07803 0.07329 -0.0155 0.0865 1.0000
8.000 0.8120 0.08156 0.07713 -0.0184 0.0836 1.0000
8.250 0.8044 0.08599 0.08163 -0.0206 0.0806 1.0000
8.500 0.7072 0.08599 0.08194 -0.0205 0.0983 1.0000
8.750 0.6939 0.09187 0.08778 -0.0246 0.0979 1.0000
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Polar data table (+)
Polar graphs
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