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

Item

Title
The Effect of Surface Perturbations on the Pressure Distributions About Blunt Two-Dimensional Bodies at High Mach Numbers
Date
1964
Index Abstract
Coming Soon
Photo Quality
Not Needed
Report Number
FDL TDR 64-17
Creator
Donaldson, Coleman duP.
Sullivan, Roger D.
Hayes, Wallace D.
Corporate Author
Aeronautical Research Associates of Princeton, Inc.
Laboratory
AF Flight Dynamics Laboratory
Extent
70
Identifier
AD0604036
Access Rights
Notice(s)
Distribution Classification
1
Contract
AF 33(657)-7313
DoD Project
8219
DoD Task
821902
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Abstract
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.
Report Availability
Full text available by request
Date Issued
1964-04
Type
report
Provenance
Lockheed Martin Missiles & Fire Control
Format
70 pages ; 28 cm.