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Wind-tunnel investigation of effect of yawing on lateral-stability characteristics II : rectangular N.A.C.A. 23012 wing with a circular fuselage

M J Bamber, R G House

Abstract

Note presenting testing of an N.A.C.A. 23012 rectangular wing with rounded tips in combination with a fuselage of circular cross section at several angles of yaw in the NACA 7- by 10-foot wind tunnel. The model was tested as a high-wing, a midwing, and a low-wing monoplane; for each wing location, tests were made with two amounts of dihedral and with partial-span split flaps. Results regarding the wing and fuselage, fin and fuselage, and wing, fuselage, and fin are provided.

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Available abstract

Key concepts: Fuselage, Wing, Structural engineering, Wind tunnel, Fin, Wing twist, Aeroelasticity, Wing configuration