Separated flow induced by trailing-edge flaps on delta wings at M = 8.2

Rao, DM (1975) Separated flow induced by trailing-edge flaps on delta wings at M = 8.2. Journal of Aeronautical Society of India, 27. pp. 17-21.

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Flow separation phenomena on the wind-ward surface of delta wings, caused by full-span trailing-edge flap deflection were studied in a 8-in-diam tunnel at Mach 8.2. Surface flow visualization, together with static pressure and overall aerodynamic load measurements were made on two models with 70- and 76-degree leading-edge sweep angles respectively, at various incidence and flap deflection angles. Some effects associated with the Reynolds number were also studied. The overall forces with deflected flaps were compared with simple theoretical predictions; the salient features of three-dimensional separation patterns are interpreted in an attempt to obtain a physical description of the flow field.

Item Type: Article
Uncontrolled Keywords: Flaps;Deflection;Aerodynamics;Delta wings;Angle of incidence;Mathematical models;Separation;Aeronautics;Loads (forces);Reynolds number;Fields (physics);Computational fluid dynamics;Tunnels (transportation);Static pressure; Fluid flow;Aerodynamics;Delta wings;Separated flow;Training edge flaps
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Users 90 not found.
Date Deposited: 23 Jan 2007
Last Modified: 24 May 2010 04:24

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