On a Solution of the Nonlinear Differential Equation for Transonic Flow Past a Wave-shaped Wall
On a Solution of the Nonlinear Differential Equation for Transonic Flow Past a Wave-shaped Wall

Author: Carl Kaplan

Publisher:

Published: 1951

Total Pages: 42

ISBN-13:

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The simplified nonlinear differential equation for transonic flow past a wavy wall is solved by the method of integration in series. The solution has been carried to the point where the question of the existence or nonexistence of a mixed potential flow can be answered by the behavior of a single power series in the transonic similarity parameter. The calculation of the coefficient of this dominant power series has been reduced to a routine computing problem by means of recursion formumlas resulting from the solution of the differential equation and the boundary condition at the surface of the wavy wall.

On Transonic Flow Past a Wave-shaped Wall
On Transonic Flow Past a Wave-shaped Wall

Author: Carl Kaplan

Publisher:

Published: 1952

Total Pages: 52

ISBN-13:

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The simplified nonlinear differential equation for transonic flow past a wavy wall is solved by the method of integration in series. A general procedure for the solution of the resulting recurrence formulas is shown and illustrated by a number of examples. A numerical test of convergence is applied to a key power series in k, the transonic similartiy parameter, and leads to the conclusion that smooth symmetrical potential flow past the wavy wall is no longer possible when the critical value of the stream Mach number is exceeded.

Report
Report

Author: United States. National Advisory Committee for Aeronautics

Publisher:

Published: 1953

Total Pages: 24

ISBN-13:

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Rectangular-wind-tunnel Blocking Corrections Using the Velocity-ratio Method
Rectangular-wind-tunnel Blocking Corrections Using the Velocity-ratio Method

Author: Rudolph W. Hensel

Publisher:

Published: 1951

Total Pages: 708

ISBN-13:

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Calculations of the ratios of the velocity increments at test bodies to those at the tunnel walls caused by the solid blocking of these bodies within the walls of a closed rectangular wind tunnel are presented. The boides treated include two-dimensional airfoils; small bodies of revolution; straight, untapered, finite-span wings of varying span; and swept, untapered, finite-span wings of varying span. It is shown that, after wake blocking effects have been removed , the present method furnishes semiempirical blocking corrections for most wind-tunnel models and their components. The test section proportions of the Southern California Cooperative Wind Tunnel at CIT (ratio of height to width equal to 1/square root of 2) are used in the calculations.