SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)
SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) - NASA SC(2)-0714 airfoil (Ref. NASA TP-2890)
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(nasasc2-0714-il) SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) NASA SC(2)-0714 airfoil (Ref. NASA TP-2890) Max thickness 13.9% at 37% chord. Max camber 2.5% at 80% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) These coordinates are actual model coordinates, not coordinates as designed. From NASA TP-2890 1.000 -.0104 0.99 -.0071 0.98 -.0039 0.97 -.0009 0.95 .0049 0.92 .0131 0.9 .0181 0.87 .0251 0.85 .0294 0.82 .0353 0.800 .0389 0.77 .0439 0.75 .0469 0.72 .0509 0.7 .0533 0.68 .0555 0.65 .0585 0.62 .0610 0.6 .0625 0.57 .0645 0.55 .0656 0.53 .0666 0.50 .0678 0.48 .0684 0.45 .0692 0.43 .0695 0.4 .0697 0.38 .0698 0.35 .0696 0.33 .0692 0.3 .0685 0.27 .0673 0.25 .0664 0.22 .0646 0.2 .0632 0.17 .0606 0.15 .0585 0.12 .0548 0.1 .0518 0.07 .0462 0.05 .0411 0.04 .0381 0.03 .0343 0.02 .0293 0.01 .0219 0.005 .0158 0.002 .0095 0.00 .00 0.002 -.0093 .005 -.016 0.01 -.0221 0.02 -.0295 0.03 -.0344 0.04 -.0381 0.05 -.0412 0.07 -.0462 0.1 -.0517 0.12 -.0547 0.15 -.0585 0.17 -.0606 0.20 -.0633 0.22 -.0647 0.25 -.0666 0.28 -.068 0.3 -.0687 0.32 -.0692 0.35 -.0696 0.37 -.0696 0.4 -.0692 0.42 -.0688 0.45 -.0676 0.48 -.0657 0.5 -.0644 0.53 -.0614 0.55 -.0588 0.58 -.0543 0.6 -.0509 0.63 -.0451 0.65 -.041 0.68 -.0346 0.70 -.0302 0.73 -.0235 0.75 -.0192 0.77 -.0150 0.80 -.0093 0.83 -.0048 0.85 -.0024 0.87 -.0013 0.89 -.0008 0.92 -.0016 0.94 -.0035 0.95 -.0049 0.96 -.0066 0.97 -.0085 0.98 -.0109 0.99 -.0137 1.0 -.0163 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nasasc2-0714-il | 50,000 | 9 | 24.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 50,000 | 5 | 22.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 100,000 | 9 | 28.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 100,000 | 5 | 31.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 200,000 | 9 | 36.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 200,000 | 5 | 43.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 500,000 | 9 | 66 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 500,000 | 5 | 64 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nasasc2-0714-il | 1,000,000 | 9 | 83.7 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nasasc2-0714-il | 1,000,000 | 5 | 80 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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