The Application of Green's Theorem to the Solution of Boundary-value Problems in Linearized Supersonic Wing Theory PDF Download
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Author: Max A. Heaslet Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 656
Book Description
Under the assumptions of linearized theory, general methods of solutin are given for two- and three-dimensional steady-state and two-dimensional unsteady-state equations of compressible flow. The solutions depend in all cases on the use of Green's equivalent layer of sources, sinks, and doublets. Emphasis is placed on applications in supersonic wing theory, the singularities arising in the integrations being treated by Hadamard's finite part of the technique. Four examples of different character are discussed. In particular, the load distribution over a specific swept-back lifting surface is determined at a free-stream Mach number of one.
Author: Max A. Heaslet Publisher: ISBN: Category : Aerodynamics, Supersonic Languages : en Pages : 656
Book Description
Under the assumptions of linearized theory, general methods of solutin are given for two- and three-dimensional steady-state and two-dimensional unsteady-state equations of compressible flow. The solutions depend in all cases on the use of Green's equivalent layer of sources, sinks, and doublets. Emphasis is placed on applications in supersonic wing theory, the singularities arising in the integrations being treated by Hadamard's finite part of the technique. Four examples of different character are discussed. In particular, the load distribution over a specific swept-back lifting surface is determined at a free-stream Mach number of one.
Author: Harvard Lomax Publisher: ISBN: Category : Aerofoils Languages : en Pages : 38
Book Description
The damping-in-roll parameter C(iota)(p) is calculated theoretically for triangular wings on cylindrical bodies and for a class of wings with sweptback plan forms. The analysis is based on the usual assumptions of linearized compressible-flow theory together with the added restrictions that at the free-stream Mach number M(omicron) the product of lM(omicron)(2) and the streamwise velocity gradient is small.
Author: Fred M. Reinhart Publisher: ISBN: Category : Aluminum alloys Languages : en Pages : 766
Book Description
Corrosion behaviro of spot-welded aluminum-alloy (alclad 24S-T3, 24S-T3, alclade XB75S-T6, XB75S-T6, and R-301-T6) panels of varying weld quality was determined. Tidewater and weather exposure tests were made and the results were evaluated largely in terms of distribution of corrosion products and effects on weld strength. Metallographic examinations of several of the alloys were also made to determine the extent and type of corrosion attack associated with various welding and exposure conditions.
Author: Max A. Heaslet
Author: Max A. Heaslet
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: Dwight G. Moore
Author: Harvard Lomax
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: Fred M. Reinhart