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Numerical Calculation of Transonic Flow about Slender Bodies of Revolution

Author : Frank R. Bailey

Publisher :

Page : 44 pages

File Size : 19,92 MB

Release : 1971

Category : Aerodynamics, Transonic

ISBN :

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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 : 38,18 MB

Release : 1959

Category : Aerodynamics

ISBN :

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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.









Theoretical Investigation of Transonic Similarity for Bodies of Revolution

Author : W. Perl

Publisher :

Page : 38 pages

File Size : 12,86 MB

Release : 1950

Category : Air flow

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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.





Analysis of Transonic Flow about Lifting Wing-body Configurations

Author : Richard W. Barnwell

Publisher :

Page : 82 pages

File Size : 38,30 MB

Release : 1975

Category : Aerodynamics, Transonic

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Book Description

An analytical solution is obtained for the perturbation velocity potential for transonic flow about lifting wing-body configurations with order-one span-length ratios and small reduced-span-length ratios and equivalent-thickness-length ratios. The analysis is performed with the method of matched asymptotic expansions. The angles of attack which are considered are small but are large enough to insure that the effects of lift in the region far from the configuration are either dominant or comparable with the effects of thickness. The modification to the equivalence rule which accounts for these lift effects is determined. An analysis of transonic flow about lifting wings with large aspect ratios is also presented.



Experimental Study of the Equivalence of Transonic Flow about Slender Cone-cylinders of Circular and Elliptic Cross Section

Author : William A. Page

Publisher :

Page : 668 pages

File Size : 33,99 MB

Release : 1958

Category : Aerodynamics, Transonic

ISBN :

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Book Description

The results of the investigation suggest that at transonic speeds and at small angles of attack the calculation of all aerodynamic characteristics of slender, three-dimensional shapes can be made by use of transonic slender-body theory when the pressures on the equivalent body of revolution are Imown, either by experiment, or by an adequate nonlinear theory. From transonic slender-body theory it is deduced that the slenderness required for this application is the same as that required for the successful application of the transonic area rule.