An Integral Equation Technique for Evaluating the Aerodynamic Characteristics of Bodies of Revolution in Curved Flight PDF Download

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1982 1982

An Integral Equation Technique for Evaluating the Aerodynamic Characteristics of Bodies of Revolution in Curved Flight

Author: A. Mohammed
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Book Description

An Integral Equation Technique for Evaluating the Aerodynamic Characteristics of Bodies of Revolution in Curved Flight

Author: A. Mohammed
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Book Description

A Method for Obtaining the Nonlinear Aerodynamic Stability Characteristics of Bodies of Revolution from Free-flight Tests

Author: Donn B. Kirk
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52

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Book Description

Aerodynamic Assessment of Flight-Determined Subsonic Lift and Drag Characteristics of Seven Lifting-Body and Wing-Body Reentry Vehicle Configurations

Author: Edwin J. Saltzman
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 162

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Book Description

Equations for the Newtonian Static and Dynamic Aerodynamic Coefficients for a Body of Revolution with an Offset Center-of-gravity Location

Author: Robert C. Ried
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 32

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Book Description

A Ring Source Method for Predicting the Aerodynamic Characteristics of Bodies of Revolution

Author: P. A. T. Christopher
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 100

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Book Description

Scientific and Technical Aerospace Reports

Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 324

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Book Description

Calculation of Compressible Potential Flow Past Slender Bodies of Revolution by an Integral Method

Author: Milton M. Klein
Publisher:
ISBN:
Category : Air flow
Languages : en
Pages : 60

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Book Description
An integral method, previously used to obtain compressible flow past two-dimensional shapes, is applied to the calculation of compressible potential flow past slender bodies of revolution. Good agreement of the resulting velocities on ellipsoids of revolution with those obtained by other methods was found. Flow-field conditions, in particular, local supersonic regions, are calculated and discussed. The free-stream Mach number beyond which a continuous potential-flow solution ceases to exist is found to be very close to 1.

Effect of Cross-section Shape on the Aerodynamics Characteristics of Bodies at Mach Numbers from 2.50 to 4.63

Author: Dennis E. Fuller
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 40

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Book Description

A Wind-tunnel Investigation of the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.98, and 3.90 at Angles of Attack to 90 Deg

Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 40

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Book Description

Asymmetric Lateral-directional Characteristics of Pointed Bodies of Revolution at High Angles of Attack

Author: Paul L. Coe
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 52

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Book Description