NACA 64-206 (naca64206-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-206 (naca64206-il) Reynolds number: 50,000 Max Cl/Cd: 30.13 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64206-il-50000-n5.txt Download as CSV file: xf-naca64206-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5821 0.10395 0.09736 -0.0080 1.0000 0.0999
-8.250 -0.5653 0.09902 0.09227 -0.0048 1.0000 0.1100
-8.000 -0.5771 0.09616 0.08970 -0.0108 1.0000 0.1130
-7.750 -0.5641 0.09192 0.08533 -0.0079 1.0000 0.1227
-7.250 -0.5625 0.08430 0.07783 -0.0148 1.0000 0.1387
-6.750 -0.4833 0.05735 0.05099 -0.0285 1.0000 0.0581
-6.500 -0.5242 0.06563 0.05872 -0.0295 1.0000 0.0558
-6.250 -0.5123 0.06082 0.05375 -0.0316 1.0000 0.0517
-6.000 -0.4945 0.05598 0.04844 -0.0341 1.0000 0.0449
-5.750 -0.4792 0.05172 0.04401 -0.0349 1.0000 0.0431
-5.500 -0.4614 0.04758 0.03956 -0.0357 1.0000 0.0414
-5.250 -0.4413 0.04361 0.03519 -0.0363 1.0000 0.0401
-5.000 -0.4193 0.03984 0.03094 -0.0365 1.0000 0.0391
-4.750 -0.3959 0.03646 0.02706 -0.0365 1.0000 0.0387
-4.500 -0.3714 0.03335 0.02343 -0.0361 1.0000 0.0389
-4.250 -0.3465 0.03082 0.02042 -0.0356 1.0000 0.0419
-4.000 -0.3203 0.02872 0.01769 -0.0349 1.0000 0.0470
-3.750 -0.2959 0.02625 0.01501 -0.0340 1.0000 0.0491
-3.500 -0.2713 0.02432 0.01287 -0.0327 1.0000 0.0516
-3.250 -0.2476 0.02275 0.01109 -0.0312 1.0000 0.0548
-3.000 -0.2240 0.02146 0.00939 -0.0297 1.0000 0.0591
-2.750 -0.2012 0.02035 0.00815 -0.0289 1.0000 0.0732
-2.500 -0.1779 0.01910 0.00690 -0.0283 1.0000 0.0912
-2.250 -0.1533 0.01742 0.00561 -0.0282 1.0000 0.1601
-2.000 -0.1191 0.01439 0.00551 -0.0242 1.0000 1.0000
-1.750 -0.1033 0.01426 0.00502 -0.0227 1.0000 1.0000
-1.500 -0.0847 0.01419 0.00453 -0.0216 1.0000 1.0000
-1.250 -0.0645 0.01415 0.00420 -0.0209 1.0000 1.0000
-1.000 -0.0433 0.01415 0.00395 -0.0202 1.0000 1.0000
-0.750 -0.0216 0.01418 0.00377 -0.0197 1.0000 1.0000
-0.500 0.0003 0.01425 0.00366 -0.0192 1.0000 1.0000
-0.250 0.0225 0.01434 0.00361 -0.0187 1.0000 1.0000
0.000 0.0446 0.01447 0.00358 -0.0183 1.0000 1.0000
0.250 0.0667 0.01462 0.00365 -0.0179 1.0000 1.0000
0.500 0.0887 0.01481 0.00377 -0.0175 1.0000 1.0000
0.750 0.1105 0.01503 0.00395 -0.0172 1.0000 1.0000
1.000 0.1320 0.01528 0.00420 -0.0169 1.0000 1.0000
1.250 0.1542 0.01557 0.00452 -0.0168 0.9994 1.0000
1.500 0.1946 0.01599 0.00501 -0.0202 0.9875 1.0000
1.750 0.2344 0.01638 0.00553 -0.0234 0.9756 1.0000
2.000 0.2734 0.01676 0.00609 -0.0263 0.9633 1.0000
2.250 0.3125 0.01714 0.00677 -0.0292 0.9509 1.0000
2.500 0.3520 0.01751 0.00742 -0.0321 0.9384 1.0000
2.750 0.3918 0.01787 0.00814 -0.0348 0.9250 1.0000
3.000 0.4328 0.01817 0.00889 -0.0375 0.9090 1.0000
3.250 0.4954 0.01644 0.00765 -0.0358 0.7582 1.0000
3.500 0.5044 0.01747 0.00691 -0.0278 0.3508 1.0000
3.750 0.5158 0.02091 0.00852 -0.0264 0.0981 1.0000
4.000 0.5385 0.02246 0.01004 -0.0257 0.0729 1.0000
4.250 0.5613 0.02403 0.01176 -0.0248 0.0641 1.0000
4.500 0.5867 0.02566 0.01367 -0.0237 0.0591 1.0000
4.750 0.6144 0.02759 0.01581 -0.0227 0.0544 1.0000
5.000 0.6411 0.02966 0.01826 -0.0221 0.0454 1.0000
5.250 0.6686 0.03214 0.02108 -0.0214 0.0417 1.0000
5.500 0.6945 0.03508 0.02440 -0.0206 0.0400 1.0000
5.750 0.7183 0.03848 0.02822 -0.0198 0.0389 1.0000
6.000 0.7399 0.04222 0.03244 -0.0190 0.0384 1.0000
6.250 0.7573 0.04667 0.03730 -0.0183 0.0373 1.0000
6.500 0.7747 0.04991 0.04130 -0.0172 0.0356 1.0000
6.750 0.7884 0.05388 0.04588 -0.0165 0.0338 1.0000
7.000 0.7989 0.05828 0.05073 -0.0161 0.0331 1.0000
7.250 0.8067 0.06286 0.05566 -0.0160 0.0335 1.0000
7.500 0.8114 0.06756 0.06065 -0.0163 0.0340 1.0000
7.750 0.8135 0.07226 0.06556 -0.0168 0.0346 1.0000
8.000 0.8127 0.07706 0.07052 -0.0177 0.0351 1.0000
8.250 0.8104 0.08178 0.07534 -0.0188 0.0357 1.0000
8.500 0.8074 0.08647 0.08009 -0.0199 0.0363 1.0000
9.000 0.7922 0.09668 0.09043 -0.0267 0.0397 1.0000
9.250 0.7849 0.10381 0.09751 -0.0335 0.0417 1.0000
9.500 0.7819 0.10972 0.10336 -0.0375 0.0437 1.0000
9.750 0.7817 0.11508 0.10867 -0.0403 0.0461 1.0000
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Polar data table (+)
Polar graphs
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