Wing Theory in Supersonic Flow
Wing Theory in Supersonic Flow

Author: Elie Carafoli

Publisher: Elsevier

Published: 2013-10-22

Total Pages: 611

ISBN-13: 1483160270

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Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.

Second-Order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradients
Second-Order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradients

Author: PETER G. WILBY

Publisher:

Published: 1961

Total Pages: 1

ISBN-13:

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The three-dimensional perturbation velocities over an infinite thin wing with a sharp leading edge in non-uniform supersonic flow are derived and used to investigate the second-order contribution to the pressure coefficient on a wing surface, due to a spanwise entropy gradient. Pressure distributions are calculated for a wedge section wing at various Mach numbers for probable values of entropy gradient. Results show that entropy gradient effects can be important. Procedure for application of the theory is given for the case of a wing situated behind the curved shock generated by a blunt nosed body. (Author).

Flow Separation
Flow Separation

Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development

Publisher:

Published: 1975

Total Pages: 594

ISBN-13:

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On Slender Delta Wings with Leading-edge Separation
On Slender Delta Wings with Leading-edge Separation

Author: Clinton E. Brown

Publisher:

Published: 1955

Total Pages: 27

ISBN-13:

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The computations show that leading-edge separation produces an increase in lift over that given by the Jones slender-wing theory and that the lift does not vary linearly with angle of attack. Computed pressure distributions and span loadings are presented and the theoretical lift results are compared with the results of simple force tests made at a Mach number of 1.9.