Conically cambered delta wings in supersonic flow. II - Optimal solutions

Bera, Rajendra K and Ramachandra, SM (1979) Conically cambered delta wings in supersonic flow. II - Optimal solutions. Aeronautical Society of India, Journal, 29. pp. 145-148.

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The simplicity of the results and favorable properties of a class of conically cambered delta wings with subsonic leading edges in a supersonic stream, studied in Part I, has suggested that one look into the possibility of obtaining useful minimum drag shapes when the basic solutions are linearly combined in a Lagrange multiplier formulation. To this end, the classical problem of minimum drag wings for a given total lift is solved by linearly combining the basic twist distributions in combinations of two, three and four using the Lagrange multiplier method. The optimal conical surfaces reported appear to be of practical use because of small surface waviness and a washout in incidence near the leading edge. The lift-to-drag ratios are close to the plane delta with suction and their off-design properties are expected to be better than those of Tsien (1955) and Holla (1967). The simplicity of the conical surfaces make them a viable candidate for any delta wing design for supersonic flight.

Item Type: Article
Uncontrolled Keywords: Cambered wings;Conical camber;Delta wings;Supersonic flow;Drag reduction;Lift;Lift drag ratio
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Ms. Alphones Mary
Date Deposited: 09 May 2006
Last Modified: 24 May 2010 04:10

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