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Wind Tunnel Tests of Ailerons at Various Speeds V : Pressure Distributions over the NACA 66,2-216 and NACA 23012 Airfoils with Various Balances on 0.20-chord Ailerons

H. G. Denaci

Abstract

Report presenting pressure distribution testing of an NACA 66,2-216, a = 1.0 airfoil equipped with a blunt nose balance aileron and a sealed internal-balance aileron and of an NACA 23012 airfoil equipped with a Frise aileron and a blunt nose balance aileron in the stability tunnel. Results regarding the section pressure distribution and section loads and moments are provided.

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Key concepts: Aileron, Airfoil, Wind tunnel, NACA airfoil, Chord (peer-to-peer), Angle of attack, Mechanics, Structural engineering