NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il)
NASA/LANGLEY RC08-64C AIRFOIL - NASA/Langley 08-64C rotorcraft airfoil
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(rc0864c-il) NASA/LANGLEY RC08-64C AIRFOIL NASA/Langley 08-64C rotorcraft airfoil Max thickness 8% at 40% chord. Max camber 1% at 35% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY RC08-64C AIRFOIL
35. 35.
0.0 0.0
0.00034 0.00700
0.01016 0.01245
0.01152 0.01308
0.02391 0.01830
0.03808 0.02245
0.04891 0.02506
0.05744 0.02689
0.07386 0.02993
0.08010 0.03099
0.09887 0.03383
0.13206 0.03791
0.14904 0.03968
0.19927 0.04387
0.22293 0.04538
0.24952 0.04679
0.28937 0.04838
0.29976 0.04870
0.32348 0.04929
0.35000 0.04971
0.40002 0.04986
0.46380 0.04887
0.50048 0.04776
0.57368 0.04437
0.60058 0.04278
0.64943 0.03947
0.70053 0.03543
0.76516 0.02950
0.80040 0.02590
0.84332 0.02116
0.90022 0.01430
0.92185 0.01153
0.95011 0.00778
0.96105 0.00629
1.00000 0.00080
0.0 0.0
0.00034 -.00585
0.01016 -.00975
0.01348 -.01088
0.02609 -.01424
0.03808 -.01666
0.05109 -.01836
0.05744 -.01912
0.07614 -.02087
0.08010 -.02120
0.10113 -.02263
0.13206 -.02424
0.15096 -.02506
0.20073 -.02672
0.22293 -.02734
0.25048 -.02801
0.28937 -.02881
0.30024 -.02900
0.32348 -.02937
0.35000 -.02971
0.39980 -.03014
0.46380 -.03019
0.49952 -.02994
0.53656 -.02946
0.59941 -.02809
0.64943 -.02642
0.69947 -.02427
0.76516 -.02065
0.79960 -.01842
0.84332 -.01524
0.89978 -.01060
0.92185 -.00861
0.94989 -.00596
0.96105 -.00485
1.00000 -.00080
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Polars for NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc0864c-il | 50,000 | 9 | 23.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 50,000 | 5 | 25.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc0864c-il | 100,000 | 9 | 37.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 100,000 | 5 | 31.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc0864c-il | 200,000 | 9 | 44 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 200,000 | 5 | 33.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc0864c-il | 500,000 | 9 | 42.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 500,000 | 5 | 40.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc0864c-il | 1,000,000 | 9 | 45.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 1,000,000 | 5 | 46.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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