SC(2)-0714 | Supercritical airfoil (coordinates from Raymer w/ one correction). These coordinates are actual model coordinates, not coordinates as designed. Ref: NASA TP-2890 Airfoil
nasasc2-0714Properties
Plot Type
Ncrit
Reynolds Numbers
Kulfan Parameters
Airfoil Geometry
SC(2)-0714 | Supercritical airfoil (coordinates from Raymer w/ one correction). These coordinates are actual model coordinates, not coordinates as designed. Ref: NASA TP-2890 at a glance
At a Reynolds number of 1,000,000 the SC(2)-0714 | Supercritical airfoil (coordinates from Raymer w/ one correction). These coordinates are actual model coordinates, not coordinates as designed. Ref: NASA TP-2890 reaches a maximum lift coefficient of 1.82 at 16.5° angle of attack, a best lift-to-drag ratio of 87 at Cl 0.55 (-0.5°), and a minimum drag coefficient of 0.0060. It carries zero lift at -4.8°.
| Reynolds number | 200,000 | 1,000,000 | 5,000,000 |
|---|---|---|---|
| Max Clthe stall peak | 1.39 | 1.82 | 2.23 |
| at alphaangle of attack it occurs at | 10.5° | 16.5° | 21.0° |
| Best L/Dhighest lift-to-drag ratio | 36 |
Performance Metrics
These curves are computed with NeuralFoil, a neural network trained on XFOIL, from a stored sweep across Reynolds number, Ncrit and angle of attack. How the polars are computed, and where they stop being trustworthy →
Run it at your Reynolds number
The curves above are a stored sweep at fixed Reynolds numbers. Enter the one your chord and speed actually give and NeuralFoil computes that polar now, onto this chart.
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Aircraft Usage
Found in UIUC Database
No specific aircraft mappings found for "nasasc2-0714" in the current database.
Sections like the SC(2)-0714 | Supercritical airfoil (coordinates from Raymer w/ one correction). These coordinates are actual model coordinates, not coordinates as designed. Ref: NASA TP-2890
The five closest shapes in the library, by maximum thickness and camber and where along the chord each falls.
- NASA SC(2)-0714 AIRFOIL14.0% thick · 2.5% camber
- NASA SC(2)-0614 AIRFOIL14.0% thick · 2.1% camber
- DFVLR R-4 AIRFOIL13.4% thick · 2.1% camber
- NASA SC(2)-0712 AIRFOIL12.0% thick · 2.2% camber
- NASA SC(2)-0612 AIRFOIL12.0% thick · 1.9% camber
Ranked on geometry alone, from the stored CST parameters — no polar is consulted, so a section that sits close here can still behave differently at the Reynolds number you fly. A near-symmetric section is matched on thickness and its distribution only: with no camber to speak of, where its camber peaks is rounding error rather than shape.