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Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap

Arthur R Wallace

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Abstract

I?ACAACR No. 4122 me pitching-momer~t-coefficient slope with flap deflected was erratlo, but the pitching-moment-coefficient slope for the plain alrfoll became slightly more negative with inoreaslng Reynolds number.

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I?ACAACR No. 4122 me pitching-momer~t-coefficient slope with flap deflected was erratlo, but the pitching-moment-coefficient slope for the plain alrfoll became slightly more negative with inoreaslng Reynolds number.

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Available abstract

I?ACAACR No. 4122 me pitching-momer~t-coefficient slope with flap deflected was erratlo, but the pitching-moment-coefficient slope for the plain alrfoll became slightly more negative with inoreaslng Reynolds number.

Key concepts: Airfoil, Chord (peer-to-peer), Lift coefficient, NACA airfoil, Pitching moment, Reynolds number, Aerodynamic center, Turbulence

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Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap — Research Paper | ScholarLens