Airfoil Details
NACA-1 COWL Airfoil
naca1Properties
NACA-1 COWL
naca1
Thickness
70.1%
Max t/c Loc
100.0%
Camber
-5.8%
Max Camber Loc
41.5%
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Plot Type
Ncrit
Reynolds Numbers
Kulfan Parameters
Airfoil Geometry
Performance Metrics
Active Scales:0 Reynolds Active
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 →
Performance polars are generated with NeuralFoil on demand. Load them to view Cl, Cd, and Cm across Reynolds numbers.
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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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Using foil.tools, compare NACA-1 COWL against SD7037 at Re 240k and tell me which one stalls more gently.
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Aircraft Usage
Found in UIUC Database
0Known Applications
No specific aircraft mappings found for "naca1" in the current database.