Computation of Transonic Flow Past Slender Bodies of Revolution
Author :
Publisher :
Page : pages
File Size : 50,36 MB
Release : 1979
Category :
ISBN :
Computation of Transonic Flow Past Slender Bodies of Revolution : Part 1, Equivalent Body, Thickness Case : Part 2, Lift Effect
Author : Yat-Yung Chan
Publisher :
Page : pages
File Size : 45,89 MB
Release : 1979
Category :
ISBN :
Book Description
Numerical Calculation of Transonic Flow about Slender Bodies of Revolution
Author : Frank R. Bailey
Publisher :
Page : 44 pages
File Size : 10,74 MB
Release : 1971
Category : Aerodynamics, Transonic
ISBN :
Book Description
A relaxation method is described for the numerical solution of the transonic small disturbance equation for flow about a slender body of revolution. Results for parabolic arc bodies, both with and without an attached sting, are compared with wind-tunnel measurements for a free-stream Mach number range from 0.90 to 1.20. The method is also used to show the effects of wind-tunnel wall interference by including boundary conditions representing porous-wall and open-jet wind-tunnel test sections.
Slender-body Theory Based on Approximate Solution of the Transonic Flow Equation
Author : John R. Spreiter
Publisher :
Page : 60 pages
File Size : 24,13 MB
Release : 1959
Category : Aerodynamics
ISBN :
Book Description
Summary: Approximate solutions of the nonlinear equations of the small disturbance theory of transonic flow are found for the pressure distribution on pointed slender bodies of revolution for flows with free-stream Mach number 1, and for flows that are either purely subsonic or purely supersonic. These results are obtained by application of a method based on local linearization that was introduced recently in the analysis of similar problems in low-dimensional flows. The theory is developed for bodies of arbitrary shapes, and specific results are given for cone-cylinders and for parabolic-arc bodies at zero angle of attack. All results are compared either with existing theoretical results or with experimental data.
Numerical Calculation of Transonic Flow about Slender Bodies of Revolution
Author : Frank R. Bailey
Publisher :
Page : 35 pages
File Size : 13,20 MB
Release : 1971
Category :
ISBN :
Book Description
Calculation of Compressible Potential Flow Past Slender Bodies of Revolution by an Integral Method
Author : Milton M. Klein
Publisher :
Page : 60 pages
File Size : 43,62 MB
Release : 1950
Category : Air flow
ISBN :
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.
Transonic Flow Over a Non-lifting, Slender Body of Revolution
Author : Winston W. Royce
Publisher :
Page : 158 pages
File Size : 29,35 MB
Release : 1959
Category : Electronic dissertations
ISBN :
Book Description
Transonic Flow Fields Around Various Bodies of Revolution Including Preliminary Studies on Viscous Effects with and Without Plume
Author : Jain-Ming Wu
Publisher :
Page : 68 pages
File Size : 16,39 MB
Release : 1971
Category : Aerodynamics, Transonic
ISBN :
Book Description
The report outlines the solution to the lifting slender body in transonic flow. Remarks are also made concerning the transonic flow past cone-cylindrical configurations. Preliminary calculations concerning viscous effects, and particularly plume induced separation, are included. (Author).
Theoretical Investigation of Transonic Similarity for Bodies of Revolution
Author : W. Perl
Publisher :
Page : 38 pages
File Size : 37,60 MB
Release : 1950
Category : Air flow
ISBN :
Book Description
Solution for compressible flow past slender bodies of revolution has been derived by an iteration procedure similar to Rayleigh-Janzen and Prandtl-Ackeret methods. Solution has been analyzed with respect to transonic similarity. Results are in approximate agreement with those of von Karman in region of flow field not to close to the body. In neighborhood of the body, a different similarity law is obtained, which holds for variations in thickness ratio and Mach number, but not for variations in specific-heat ratio. In addition, this law appears to be limited in applicability to extremely slender bodies of revolution. The differences between results of the present investigation and those of von Karman are interpreted in terms of the manner in which boundary condition on the body is satisfied and of the nature of the singularity of the solution near the axis.
NASA Technical Note
Author :
Publisher :
Page : 784 pages
File Size : 35,7 MB
Release : 1975
Category : Aeronautics
ISBN :
