NACA 64-110 AIRFOIL (n64110-il)
NACA 64-110 AIRFOIL - NACA 64-110 airfoil
| Details | Dat file | Parser | |
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(n64110-il) NACA 64-110 AIRFOIL NACA 64-110 airfoil Max thickness 10% at 40% chord. Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NACA 64-110 AIRFOIL
26. 26.
0.000000 0.000000
0.004650 0.008440
0.007120 0.010230
0.012070 0.013030
0.024500 0.017930
0.049450 0.025000
0.074430 0.030370
0.099440 0.034790
0.149470 0.041780
0.199530 0.047000
0.249590 0.050870
0.299670 0.053500
0.349750 0.054950
0.399840 0.055240
0.449920 0.053910
0.500000 0.051380
0.550070 0.047860
0.600120 0.043560
0.650160 0.038600
0.700190 0.033130
0.750200 0.027290
0.800190 0.021200
0.850160 0.015120
0.900120 0.009290
0.950060 0.004060
1.000000 0.000000
0.000000 0.000000
0.005350 -0.007940
0.007880 -0.009530
0.012930 -0.011950
0.025500 -0.016070
0.050550 -0.021840
0.075570 -0.026130
0.100560 -0.029630
0.150530 -0.035060
0.200470 -0.039040
0.250410 -0.041910
0.300330 -0.043780
0.350250 -0.044650
0.400160 -0.044520
0.450080 -0.042950
0.500000 -0.040340
0.549930 -0.036900
0.599880 -0.032840
0.649840 -0.028300
0.699810 -0.023410
0.749800 -0.018330
0.799810 -0.013240
0.849840 -0.008400
0.899880 -0.004130
0.949940 -0.000900
1.000000 0.000000
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Polars for NACA 64-110 AIRFOIL (n64110-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n64110-il | 50,000 | 9 | 29.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64110-il | 50,000 | 5 | 28.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64110-il | 100,000 | 9 | 41.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64110-il | 100,000 | 5 | 39 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64110-il | 200,000 | 9 | 54.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64110-il | 200,000 | 5 | 44.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64110-il | 500,000 | 9 | 63.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64110-il | 500,000 | 5 | 54.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64110-il | 1,000,000 | 9 | 69.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64110-il | 1,000,000 | 5 | 68.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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