NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 200,000 Max Cl/Cd: 58.86 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64208-il-200000.txt Download as CSV file: xf-naca64208-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5448 0.08768 0.08419 -0.0164 1.0000 0.0375
-8.500 -0.5473 0.08303 0.07958 -0.0199 1.0000 0.0388
-8.250 -0.5521 0.07812 0.07473 -0.0241 1.0000 0.0392
-8.000 -0.5606 0.07271 0.06933 -0.0299 1.0000 0.0396
-7.750 -0.5640 0.06761 0.06410 -0.0345 1.0000 0.0408
-7.500 -0.5639 0.06440 0.06054 -0.0374 1.0000 0.0420
-7.250 -0.5585 0.06143 0.05727 -0.0380 1.0000 0.0423
-7.000 -0.5582 0.05319 0.04911 -0.0392 1.0000 0.0439
-6.750 -0.5454 0.05076 0.04681 -0.0386 1.0000 0.0473
-6.500 -0.5333 0.04753 0.04337 -0.0388 1.0000 0.0512
-6.250 -0.5233 0.04395 0.03910 -0.0386 1.0000 0.0564
-6.000 -0.5090 0.04016 0.03545 -0.0383 1.0000 0.0587
-4.750 -0.4154 0.02420 0.01734 -0.0311 1.0000 0.0437
-4.500 -0.3945 0.02270 0.01556 -0.0295 1.0000 0.0430
-4.250 -0.3734 0.02031 0.01300 -0.0281 1.0000 0.0408
-4.000 -0.3519 0.01846 0.01092 -0.0268 1.0000 0.0405
-3.750 -0.3304 0.01715 0.00944 -0.0255 1.0000 0.0410
-3.500 -0.3091 0.01603 0.00816 -0.0243 1.0000 0.0431
-3.250 -0.2882 0.01472 0.00691 -0.0234 1.0000 0.0472
-3.000 -0.2643 0.01391 0.00608 -0.0230 0.9994 0.0505
-2.750 -0.2245 0.01293 0.00507 -0.0258 0.9947 0.0576
-2.500 -0.1853 0.01213 0.00431 -0.0285 0.9888 0.0796
-2.250 -0.1560 0.00933 0.00394 -0.0302 0.9848 0.6525
-2.000 -0.1222 0.00925 0.00407 -0.0310 0.9775 0.7397
-1.750 -0.0876 0.00930 0.00423 -0.0317 0.9708 0.7970
-1.500 -0.0616 0.00943 0.00448 -0.0300 0.9622 0.8509
-1.250 -0.0304 0.00951 0.00456 -0.0296 0.9561 0.8845
-1.000 0.0013 0.00946 0.00447 -0.0301 0.9477 0.9009
-0.750 0.0384 0.00938 0.00434 -0.0318 0.9421 0.9139
-0.500 0.0693 0.00931 0.00422 -0.0322 0.9330 0.9286
-0.250 0.1077 0.00921 0.00409 -0.0341 0.9274 0.9410
0.000 0.1433 0.00913 0.00399 -0.0355 0.9181 0.9544
0.250 0.1866 0.00903 0.00388 -0.0386 0.9120 0.9641
0.500 0.2291 0.00895 0.00380 -0.0417 0.9031 0.9742
0.750 0.2727 0.00888 0.00373 -0.0450 0.8948 0.9838
1.000 0.3176 0.00878 0.00365 -0.0487 0.8865 0.9923
1.250 0.3522 0.00875 0.00366 -0.0504 0.8748 1.0000
1.500 0.3701 0.00880 0.00371 -0.0487 0.8615 1.0000
1.750 0.3889 0.00885 0.00376 -0.0470 0.8478 1.0000
2.000 0.4099 0.00892 0.00382 -0.0456 0.8340 1.0000
2.250 0.4322 0.00891 0.00379 -0.0441 0.8166 1.0000
2.500 0.4514 0.00873 0.00355 -0.0413 0.7795 1.0000
2.750 0.4727 0.00866 0.00333 -0.0391 0.7358 1.0000
3.000 0.4976 0.00874 0.00339 -0.0382 0.7072 1.0000
3.250 0.5215 0.00886 0.00342 -0.0370 0.6630 1.0000
3.500 0.5420 0.00923 0.00345 -0.0351 0.5574 1.0000
3.750 0.5440 0.01253 0.00435 -0.0317 0.0917 1.0000
4.000 0.5667 0.01362 0.00532 -0.0310 0.0620 1.0000
4.250 0.5897 0.01463 0.00636 -0.0302 0.0527 1.0000
4.500 0.6112 0.01597 0.00764 -0.0293 0.0454 1.0000
4.750 0.6357 0.01701 0.00874 -0.0286 0.0426 1.0000
5.000 0.6606 0.01832 0.01014 -0.0279 0.0404 1.0000
5.250 0.6865 0.01989 0.01180 -0.0272 0.0391 1.0000
5.500 0.7125 0.02143 0.01343 -0.0268 0.0370 1.0000
5.750 0.7376 0.02405 0.01616 -0.0265 0.0346 1.0000
6.000 0.7635 0.02635 0.01873 -0.0258 0.0348 1.0000
6.250 0.7896 0.03028 0.02348 -0.0236 0.0414 1.0000
15.000 0.6745 0.18174 0.17882 -0.0702 0.0278 1.0000
15.250 0.6786 0.18498 0.18207 -0.0719 0.0273 1.0000
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Polar data table (+)
Polar graphs
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