NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65-206 (naca65206-il) Reynolds number: 1,000,000 Max Cl/Cd: 77.77 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65206-il-1000000.txt Download as CSV file: xf-naca65206-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5322 0.08537 0.08375 -0.0133 1.0000 0.0052
-8.000 -0.5320 0.08147 0.07986 -0.0156 1.0000 0.0052
-7.750 -0.5350 0.07756 0.07599 -0.0184 1.0000 0.0052
-7.500 -0.5320 0.07247 0.07089 -0.0242 1.0000 0.0052
-7.250 -0.5264 0.06769 0.06607 -0.0279 1.0000 0.0052
-7.000 -0.5190 0.06303 0.06135 -0.0308 1.0000 0.0052
-6.750 -0.5100 0.05844 0.05667 -0.0329 1.0000 0.0052
-6.500 -0.4995 0.05386 0.05200 -0.0343 1.0000 0.0052
-6.250 -0.4877 0.04947 0.04749 -0.0351 1.0000 0.0052
-6.000 -0.4748 0.04501 0.04289 -0.0354 1.0000 0.0052
-5.750 -0.4704 0.03657 0.03412 -0.0354 1.0000 0.0055
-5.500 -0.4588 0.03358 0.03096 -0.0347 1.0000 0.0061
-5.250 -0.4443 0.03196 0.02924 -0.0336 1.0000 0.0067
-3.750 -0.2473 0.01272 0.00808 -0.0409 0.9861 0.0084
-3.500 -0.2141 0.01027 0.00536 -0.0417 0.9841 0.0083
-3.250 -0.1799 0.00948 0.00450 -0.0430 0.9821 0.0099
-3.000 -0.1503 0.00832 0.00323 -0.0435 0.9766 0.0116
-2.750 -0.1190 0.00768 0.00254 -0.0445 0.9715 0.0140
-2.500 -0.0879 0.00734 0.00217 -0.0452 0.9657 0.0174
-2.250 -0.0590 0.00710 0.00186 -0.0455 0.9578 0.0190
-2.000 -0.0311 0.00691 0.00164 -0.0455 0.9493 0.0197
-1.750 -0.0037 0.00648 0.00110 -0.0453 0.9405 0.0301
-1.500 0.0221 0.00575 0.00086 -0.0452 0.9303 0.2001
-1.250 0.0459 0.00444 0.00070 -0.0453 0.9200 0.5782
-1.000 0.0716 0.00412 0.00069 -0.0449 0.9102 0.6866
-0.750 0.0966 0.00390 0.00071 -0.0442 0.9003 0.7753
-0.500 0.1216 0.00380 0.00074 -0.0434 0.8897 0.8273
-0.250 0.1472 0.00376 0.00076 -0.0428 0.8789 0.8556
0.000 0.1726 0.00375 0.00077 -0.0421 0.8681 0.8783
0.250 0.1987 0.00376 0.00078 -0.0416 0.8562 0.8915
0.500 0.2243 0.00379 0.00079 -0.0410 0.8394 0.9041
0.750 0.2492 0.00384 0.00078 -0.0402 0.8151 0.9166
1.250 0.2974 0.00400 0.00078 -0.0383 0.7512 0.9421
1.500 0.3197 0.00419 0.00077 -0.0369 0.6882 0.9565
1.750 0.3453 0.00444 0.00080 -0.0364 0.6194 0.9722
2.000 0.3728 0.00552 0.00103 -0.0371 0.3797 0.9912
2.250 0.3944 0.00716 0.00146 -0.0370 0.0598 1.0000
2.500 0.4209 0.00766 0.00187 -0.0368 0.0232 1.0000
2.750 0.4484 0.00785 0.00207 -0.0369 0.0211 1.0000
3.000 0.4755 0.00817 0.00242 -0.0368 0.0168 1.0000
3.250 0.5008 0.00892 0.00327 -0.0363 0.0138 1.0000
3.500 0.5235 0.01026 0.00478 -0.0354 0.0130 1.0000
3.750 0.5512 0.01036 0.00489 -0.0355 0.0124 1.0000
4.000 0.5777 0.01078 0.00535 -0.0353 0.0111 1.0000
4.250 0.6042 0.01122 0.00582 -0.0351 0.0093 1.0000
4.500 0.6303 0.01173 0.00636 -0.0349 0.0082 1.0000
4.750 0.6553 0.01265 0.00734 -0.0344 0.0074 1.0000
5.000 0.6774 0.01588 0.01093 -0.0331 0.0062 1.0000
5.250 0.7040 0.01666 0.01184 -0.0327 0.0054 1.0000
5.500 0.7258 0.02149 0.01721 -0.0307 0.0054 1.0000
9.000 0.6955 0.08850 0.08716 -0.0330 0.0064 1.0000
9.250 0.6903 0.09474 0.09340 -0.0361 0.0064 1.0000
9.500 0.6868 0.10076 0.09942 -0.0389 0.0064 1.0000
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Polar data table (+)
Polar graphs
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