NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il)
NASA/LANGLEY RC-SC2 AIRFOIL - NASA/Langley RC-SC2 rotorcraft airfoil
| Details | Dat file | Parser | |
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(rcsc2-il) NASA/LANGLEY RC-SC2 AIRFOIL NASA/Langley RC-SC2 rotorcraft airfoil Max thickness 10% at 40% chord. Max camber 0.5% at 62.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
NASA/LANGLEY RC-SC2 AIRFOIL
37. 36.
0.0 0.0
0.00200 0.00816
0.00700 0.01580
0.01200 0.01940
0.02500 0.02540
0.03700 0.02950
0.05000 0.03280
0.07500 0.03770
0.10000 0.04140
0.12500 0.04430
0.15000 0.04660
0.17500 0.04840
0.20000 0.05000
0.25000 0.05220
0.30000 0.05370
0.35000 0.05460
0.40000 0.05500
0.45000 0.05470
0.50000 0.05380
0.55000 0.05230
0.60000 0.05010
0.62500 0.04880
0.65000 0.04730
0.67500 0.04570
0.70000 0.04390
0.72500 0.04180
0.75000 0.03960
0.77500 0.03710
0.80000 0.03440
0.82500 0.03140
0.85000 0.02810
0.87500 0.02450
0.90000 0.02060
0.92500 0.01620
0.95000 0.01130
0.97500 0.00670
1.00000 0.00210
0.0 0.0
0.00700 -0.01570
0.01200 -0.01890
0.02500 -0.02380
0.03700 -0.02710
0.05000 -0.02970
0.07500 -0.03340
0.10000 -0.03620
0.12500 -0.03830
0.15000 -0.03990
0.17500 -0.04120
0.20000 -0.04230
0.25000 -0.04370
0.30000 -0.04460
0.35000 -0.04500
0.40000 -0.04470
0.45000 -0.04390
0.50000 -0.04260
0.55000 -0.04070
0.60000 -0.03830
0.62500 -0.03690
0.65000 -0.03540
0.67500 -0.03380
0.70000 -0.03200
0.72500 -0.03000
0.75000 -0.02800
0.77500 -0.02580
0.80000 -0.02340
0.82500 -0.02100
0.85000 -0.01840
0.87500 -0.01560
0.90000 -0.01280
0.92500 -0.00980
0.95000 -0.00670
0.97500 -0.00340
1.00000 0.00000
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Polars for NASA/LANGLEY RC-SC2 AIRFOIL (rcsc2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rcsc2-il | 50,000 | 9 | 24.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 50,000 | 5 | 25.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 100,000 | 9 | 37.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 100,000 | 5 | 33.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 200,000 | 9 | 49.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 200,000 | 5 | 41.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 500,000 | 9 | 54.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 500,000 | 5 | 56.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rcsc2-il | 1,000,000 | 9 | 66.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rcsc2-il | 1,000,000 | 5 | 69.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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