NACA 64-208 (naca64208-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-208 (naca64208-il) Reynolds number: 50,000 Max Cl/Cd: 31.46 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64208-il-50000-n5.txt Download as CSV file: xf-naca64208-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4626 0.10219 0.09554 -0.0143 1.0000 0.0674
-9.500 -0.4606 0.09771 0.09108 -0.0153 1.0000 0.0654
-9.250 -0.5571 0.10038 0.09346 -0.0150 1.0000 0.0551
-9.000 -0.5520 0.09616 0.08919 -0.0157 1.0000 0.0527
-8.750 -0.5515 0.09169 0.08477 -0.0180 1.0000 0.0510
-8.500 -0.5537 0.08686 0.08002 -0.0213 1.0000 0.0502
-8.250 -0.5587 0.08171 0.07494 -0.0254 1.0000 0.0491
-8.000 -0.5746 0.07501 0.06811 -0.0331 1.0000 0.0431
-7.750 -0.5744 0.07060 0.06359 -0.0347 1.0000 0.0430
-7.500 -0.5729 0.06631 0.05911 -0.0361 1.0000 0.0431
-7.250 -0.5636 0.06301 0.05592 -0.0355 1.0000 0.0474
-7.000 -0.5579 0.05881 0.05152 -0.0366 1.0000 0.0479
-6.750 -0.5497 0.05456 0.04697 -0.0373 1.0000 0.0478
-6.500 -0.5390 0.05014 0.04213 -0.0377 1.0000 0.0468
-6.250 -0.5250 0.04605 0.03755 -0.0376 1.0000 0.0459
-6.000 -0.5085 0.04236 0.03336 -0.0372 1.0000 0.0457
-5.750 -0.4899 0.03907 0.02960 -0.0366 1.0000 0.0458
-5.500 -0.4699 0.03615 0.02627 -0.0359 1.0000 0.0464
-5.250 -0.4489 0.03363 0.02339 -0.0352 1.0000 0.0480
-5.000 -0.4271 0.03162 0.02101 -0.0343 1.0000 0.0526
-4.750 -0.4038 0.02968 0.01858 -0.0333 1.0000 0.0557
-4.500 -0.3803 0.02773 0.01634 -0.0320 1.0000 0.0571
-4.250 -0.3582 0.02590 0.01439 -0.0307 1.0000 0.0595
-4.000 -0.3364 0.02454 0.01293 -0.0292 1.0000 0.0629
-3.750 -0.3150 0.02348 0.01164 -0.0276 1.0000 0.0693
-3.500 -0.2951 0.02237 0.01055 -0.0264 1.0000 0.0799
-3.250 -0.2746 0.02128 0.00938 -0.0253 1.0000 0.0892
-3.000 -0.2540 0.02021 0.00827 -0.0244 1.0000 0.1053
-2.750 -0.2339 0.01812 0.00711 -0.0244 1.0000 0.2300
-2.500 -0.2329 0.01645 0.00749 -0.0179 1.0000 0.6833
-2.250 -0.2315 0.01646 0.00779 -0.0102 1.0000 0.8054
-2.000 -0.1801 0.01675 0.00794 -0.0091 1.0000 0.9561
-1.750 -0.1340 0.01653 0.00733 -0.0136 1.0000 0.9753
-1.500 -0.0879 0.01631 0.00680 -0.0183 1.0000 0.9950
-1.250 -0.0855 0.01614 0.00648 -0.0156 1.0000 1.0000
-1.000 -0.0829 0.01606 0.00627 -0.0127 1.0000 1.0000
-0.750 -0.0708 0.01609 0.00612 -0.0113 1.0000 1.0000
-0.500 -0.0401 0.01626 0.00610 -0.0132 0.9936 1.0000
-0.250 -0.0007 0.01650 0.00617 -0.0166 0.9832 1.0000
0.000 0.0383 0.01675 0.00626 -0.0198 0.9730 1.0000
0.250 0.0777 0.01701 0.00643 -0.0230 0.9633 1.0000
0.500 0.1143 0.01725 0.00661 -0.0255 0.9525 1.0000
0.750 0.1505 0.01750 0.00683 -0.0279 0.9420 1.0000
1.000 0.1877 0.01777 0.00710 -0.0304 0.9322 1.0000
1.250 0.2276 0.01803 0.00740 -0.0333 0.9236 1.0000
1.500 0.2614 0.01831 0.00773 -0.0350 0.9127 1.0000
1.750 0.2951 0.01859 0.00814 -0.0367 0.9021 1.0000
2.000 0.3295 0.01887 0.00854 -0.0383 0.8922 1.0000
2.250 0.3652 0.01914 0.00896 -0.0401 0.8828 1.0000
2.500 0.3952 0.01945 0.00944 -0.0409 0.8710 1.0000
2.750 0.4256 0.01975 0.00994 -0.0416 0.8590 1.0000
3.000 0.4565 0.02002 0.01051 -0.0421 0.8460 1.0000
3.250 0.4876 0.02026 0.01102 -0.0426 0.8321 1.0000
3.500 0.5194 0.02039 0.01149 -0.0427 0.8163 1.0000
3.750 0.5503 0.01880 0.01002 -0.0374 0.7446 1.0000
4.000 0.5651 0.01796 0.00889 -0.0305 0.6079 1.0000
4.250 0.5717 0.01931 0.00859 -0.0251 0.2860 1.0000
4.500 0.5823 0.02227 0.01028 -0.0236 0.1193 1.0000
4.750 0.6011 0.02394 0.01176 -0.0226 0.0904 1.0000
5.000 0.6213 0.02537 0.01320 -0.0216 0.0760 1.0000
5.250 0.6436 0.02683 0.01484 -0.0205 0.0694 1.0000
5.500 0.6680 0.02837 0.01649 -0.0196 0.0638 1.0000
5.750 0.6946 0.03003 0.01828 -0.0190 0.0572 1.0000
6.000 0.7215 0.03175 0.02028 -0.0186 0.0519 1.0000
6.250 0.7490 0.03408 0.02275 -0.0182 0.0497 1.0000
6.500 0.7752 0.03701 0.02590 -0.0178 0.0484 1.0000
6.750 0.7993 0.03985 0.02924 -0.0170 0.0477 1.0000
7.000 0.8204 0.04304 0.03298 -0.0160 0.0472 1.0000
7.250 0.8383 0.04654 0.03701 -0.0150 0.0469 1.0000
7.500 0.8522 0.05013 0.04120 -0.0138 0.0458 1.0000
7.750 0.8621 0.05380 0.04542 -0.0126 0.0438 1.0000
8.000 0.8689 0.05760 0.04968 -0.0116 0.0420 1.0000
8.250 0.8722 0.06180 0.05427 -0.0108 0.0415 1.0000
8.500 0.8708 0.06627 0.05909 -0.0102 0.0417 1.0000
8.750 0.8651 0.07085 0.06395 -0.0099 0.0421 1.0000
9.000 0.8557 0.07536 0.06867 -0.0100 0.0425 1.0000
9.250 0.8413 0.07980 0.07323 -0.0103 0.0429 1.0000
9.500 0.8258 0.08465 0.07816 -0.0120 0.0434 1.0000
9.750 0.8114 0.09024 0.08379 -0.0153 0.0439 1.0000
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Polar data table (+)
Polar graphs
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