NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 500,000 Max Cl/Cd: 75.77 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64208-il-500000.txt Download as CSV file: xf-naca64208-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-208
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5528 0.08568 0.08343 -0.0165 1.0000 0.0150
-8.750 -0.5539 0.08123 0.07901 -0.0192 1.0000 0.0151
-8.500 -0.5573 0.07645 0.07426 -0.0227 1.0000 0.0154
-8.250 -0.5695 0.07018 0.06803 -0.0292 1.0000 0.0152
-8.000 -0.5747 0.06502 0.06281 -0.0333 1.0000 0.0153
-7.750 -0.5753 0.06020 0.05790 -0.0359 1.0000 0.0156
-7.500 -0.5722 0.05570 0.05328 -0.0376 1.0000 0.0159
-7.250 -0.5659 0.05145 0.04889 -0.0386 1.0000 0.0164
-7.000 -0.5568 0.04727 0.04453 -0.0390 1.0000 0.0173
-6.750 -0.5332 0.04534 0.04229 -0.0381 1.0000 0.0199
-6.500 -0.5210 0.04207 0.03874 -0.0374 1.0000 0.0200
-6.000 -0.5098 0.03012 0.02604 -0.0353 1.0000 0.0213
-5.750 -0.4956 0.02786 0.02367 -0.0341 1.0000 0.0222
-5.000 -0.4210 0.01836 0.01304 -0.0330 0.9958 0.0183
-4.750 -0.3863 0.01607 0.01043 -0.0344 0.9929 0.0187
-4.500 -0.3519 0.01465 0.00881 -0.0357 0.9892 0.0194
-4.250 -0.3175 0.01295 0.00695 -0.0373 0.9858 0.0212
-4.000 -0.2821 0.01156 0.00551 -0.0391 0.9830 0.0230
-3.750 -0.2481 0.01081 0.00469 -0.0406 0.9781 0.0248
-3.500 -0.2132 0.01016 0.00400 -0.0422 0.9730 0.0273
-3.250 -0.1770 0.00981 0.00362 -0.0441 0.9687 0.0304
-3.000 -0.1463 0.00899 0.00273 -0.0448 0.9597 0.0377
-2.750 -0.1144 0.00855 0.00226 -0.0457 0.9517 0.0511
-2.500 -0.0874 0.00718 0.00179 -0.0465 0.9419 0.2923
-2.250 -0.0634 0.00611 0.00164 -0.0463 0.9304 0.5613
-2.000 -0.0375 0.00589 0.00161 -0.0458 0.9195 0.6336
-1.750 -0.0112 0.00580 0.00156 -0.0453 0.9088 0.6707
-1.500 0.0149 0.00574 0.00153 -0.0447 0.8982 0.7068
-1.250 0.0400 0.00568 0.00158 -0.0438 0.8870 0.7506
-1.000 0.0655 0.00566 0.00161 -0.0430 0.8760 0.7797
-0.750 0.0913 0.00565 0.00162 -0.0423 0.8651 0.8005
-0.500 0.1178 0.00565 0.00159 -0.0419 0.8545 0.8138
-0.250 0.1444 0.00566 0.00157 -0.0414 0.8440 0.8256
0.000 0.1710 0.00565 0.00157 -0.0411 0.8329 0.8378
0.250 0.1976 0.00566 0.00158 -0.0407 0.8221 0.8499
0.500 0.2240 0.00568 0.00160 -0.0402 0.8115 0.8622
0.750 0.2501 0.00570 0.00162 -0.0397 0.8012 0.8750
1.000 0.2760 0.00572 0.00165 -0.0391 0.7896 0.8880
1.250 0.3012 0.00573 0.00168 -0.0384 0.7767 0.9010
1.500 0.3257 0.00575 0.00170 -0.0374 0.7612 0.9147
1.750 0.3490 0.00576 0.00168 -0.0361 0.7363 0.9296
2.000 0.3713 0.00580 0.00162 -0.0346 0.6997 0.9459
2.250 0.3980 0.00584 0.00161 -0.0342 0.6701 0.9632
2.500 0.4314 0.00593 0.00167 -0.0353 0.6429 0.9803
2.750 0.4645 0.00613 0.00171 -0.0366 0.5932 1.0000
3.000 0.4890 0.00656 0.00182 -0.0362 0.5085 1.0000
3.250 0.5078 0.00796 0.00221 -0.0354 0.2725 1.0000
3.500 0.5272 0.00960 0.00287 -0.0348 0.0585 1.0000
3.750 0.5533 0.01013 0.00335 -0.0347 0.0387 1.0000
4.000 0.5793 0.01071 0.00396 -0.0344 0.0312 1.0000
4.250 0.6053 0.01122 0.00451 -0.0342 0.0272 1.0000
4.500 0.6288 0.01222 0.00556 -0.0335 0.0241 1.0000
4.750 0.6521 0.01330 0.00673 -0.0328 0.0226 1.0000
5.000 0.6781 0.01380 0.00730 -0.0325 0.0211 1.0000
5.250 0.7027 0.01473 0.00830 -0.0320 0.0201 1.0000
5.500 0.7275 0.01578 0.00943 -0.0314 0.0192 1.0000
5.750 0.7524 0.01697 0.01071 -0.0309 0.0182 1.0000
6.000 0.7774 0.01837 0.01222 -0.0304 0.0175 1.0000
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Polar data table (+)
Polar graphs
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