NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il)
NASA/LANGLEY RC10-64C AIRFOIL - NASA/Langley 10-64C rotorcraft airfoil
| Details | Dat file | Parser | |
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(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% 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 RC10-64C AIRFOIL
33. 33.
0.0 0.0
0.00355 0.00910
0.01128 0.01611
0.02363 0.02241
0.03836 0.02754
0.04864 0.03053
0.05766 0.03282
0.07357 0.03632
0.08022 0.03759
0.09859 0.04091
0.13226 0.04569
0.14879 0.04779
0.16115 0.04907
0.19908 0.05271
0.22385 0.05448
0.24940 0.05614
0.29970 0.05842
0.32544 0.05909
0.34999 0.05964
0.40024 0.05986
0.46674 0.05860
0.50060 0.05747
0.53964 0.05551
0.60073 0.05164
0.65212 0.04745
0.70066 0.04288
0.76700 0.03556
0.80050 0.03144
0.84428 0.02560
0.90028 0.01742
0.92202 0.01045
0.95014 0.00949
1.00000 0.00100
0.0 0.0
0.00355 -.00737
0.01373 -.01391
0.02637 -.01835
0.03836 -.02132
0.05136 -.02383
0.05766 -.02478
0.07643 -.02726
0.08022 -.02769
0.10141 -.02971
0.13226 -.03205
0.15121 -.03317
0.16115 -.03373
0.20092 -.03356
0.22385 -.03648
0.25060 -.03737
0.30030 -.03872
0.32544 -.03925
0.35001 -.03964
0.39976 -.04014
0.46674 -.04004
0.49940 -.03965
0.53964 -.03884
0.59927 -.03695
0.65212 -.03450
0.69934 -.03172
0.76700 -.02676
0.79950 -.02396
0.84428 -.01970
0.89972 -.01372
0.92202 -.01112
0.94986 -.00767
1.00000 -.00100
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Polars for NASA/LANGLEY RC10-64C AIRFOIL (rc1064c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc1064c-il | 50,000 | 9 | 31.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 50,000 | 5 | 30.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 100,000 | 9 | 45.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 100,000 | 5 | 41.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 200,000 | 9 | 57.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 200,000 | 5 | 46.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 500,000 | 9 | 62.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 500,000 | 5 | 59.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 1,000,000 | 9 | 71.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 1,000,000 | 5 | 73.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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