Author: George K. MorikawaPublisher:
ISBN:
Category : Electronic dissertations
Languages : en
Pages : 138
Book Description
The Wing-body Problem for Linearized Supersonic Flow
Author: George K. MorikawaPublisher:
ISBN:
Category : Electronic dissertations
Languages : en
Pages : 138
Book Description
The Wing-body Interference Problem for Linearized Supersonic Flow
Author: Michael Chen-Chiang FongPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
Book Description
Wing Theory in Supersonic Flow
Author: Elie CarafoliPublisher: Elsevier
ISBN: 1483160270
Category : Technology & Engineering
Languages : en
Pages : 611
Book Description
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.
On the Determination of Certain Basic Types of Supersonic Flow Fields
Author: Carlo FerrariPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
Book Description
Abstract: A discussion is given of the application of Fourier series techniques to the problems of linearized supersonic flow. The formulation presented is an extension of the doublet type of "fundamental solution" to higher order types of singularity. The equations developed have application to wing theory but are primarily of importance in wing-body interaction problems. A specific example of a wing-body interference problem is discussed in light of the presented methods.
Wing-body Interaction in Linear Supersonic Flow
Author: Abraham CharnesAn Improved Method for the Aerodynamic Analysis of Wing-body-tail Configurations in Subsonic and Supersonic Flow: Computer program description
Author: F. A. WoodwardPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 324
Book Description
A new method has been developed for calculating the pressure distribution and aerodynamic characteristics of wing-body-tail combinations in subsonic and supersonic potential flow. A computer program has been developed to perform the numerical calculations. The configuration surface is subdivided into a large number of panels, each of which contains an aerodynamic singularity distribution. A constant source distribution is used on the body panels, and a vortex distribution having a linear variation in the streamwise direction is used on the wing and tail panels. The normal components of velocity induced at specified control points by each singularity distribution are calculated and make up the coefficients of a system of linear equations relating the strengths of the singularities to the magnitude of the normal velocities.
An Improved Method for the Aerodynamic Analysis of Wing-body-tail Configurations in Subsonic and Supersonic Flow
Author: F. A. WoodwardPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 140
Book Description
A new method has been developed for calculating the pressure distribution and aerodynamic characteristics of wing-body-tail combinations in subsonic and supersonic potential flow. A computer program has been developed to perform the numerical calculations. The configuration surface is subdivided into a large number of panels, each of which contains an aerodynamic singularity distribution. A constant source distribution is used on the body panels, and a vortex distribution having a linear variation in the streamwise direction is used on the wing and tail panels. The normal components of velocity induced at specified control points by each singularity distribution are calculated and make up the coefficients of a system of linear equations relating the strengths of the singularities to the magnitude of the normal velocities.
An Integrated Approach to the Analysis and Design of Wings and Wing-body Combinations in Supersonic Flow
Author: Ralph L. CarmichaelPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 18
Book Description
An Analysis of the Stability and Ultimate Compressive Strength of Short Sheet-stringer Panels with Special Reference to the Influence of the Riveted Connection Between Sheet and Stringer
Author: Benjamin H. BeamPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 312
Book Description
A Method for Calculating the Aerodynamic Loading on Wing-body Combinations at Small Angles of Attack in Supersonic Flow
Author: Charlie M. JacksonPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
This report describes a theoretical method for estimating the aerodynamic loading on a wing-body configuration. In order to provide a basis for evaluation of the method, experimental measurements of surface pressures, forces, and moments were made on a series of basic wing-body configurations over a Mach number range from 2.5 to 4.5. Comparison of the theoretical estimates with these experimental data generally indicated good agreement for the entire range of configurations and test conditions.