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The Effect of Surface Perturbations on the Pressure Distributions About Blunt Two-Dimensional Bodies at High Mach Numbers

Report Number: FDL TDR 64-17
Author: Donaldson, Coleman duP.
Author: Sullivan, Roger D.
Author: Hayes, Wallace D.
Corporate Author: Aeronautical Research Associates of Princeton, Inc.
Laboratory: AF Flight Dynamics Laboratory
Date of Publication: 1964-04
Pages: 70
Contract: AF 33(657)-7313
Project: 8219
Task: 821902
AD Number: AD0604036

A method which is simpler and easier to apply than the general method of characteristics is developed for computing the pressure distributions about blunt bodies at high Mach number. The method presented enables one to compute the change in pressure distribution that results when a basic shape whose pressure distribution and flow field are known is perturbed in some manner, either by deflection of a control surface or by an aeroelastic deformation. In order to illustrate the character of this perturbation problem, the linearized theory of the pressure distribution upon a perturbed flat plate above which exists an entirely supersonic entropy layer is developed in some detail and applied to the special case of the computation of flap effectiveness on blunt wedge airfoils at infinite Mach number. With the background of these results from the linearized theory, the more general problem is discussed and an empirical method is suggested for computing the pressure distribution about a perturbed basic shape whose pressure distribution and flow field are known. The method is then used to compute the pressure distribution about a blunt two-dimensional airfoil for which theoretical and experimental pressure distributions have been obtained at M = 5 and M = approx. 8. Comparison of the method with both exact theory and experimental results shows satisfactory agreement for this particular case.

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