Turbulent Wall Pressure Fluctuations Under Separated Supersonic and Hypersonic Flows

Item

Title
Turbulent Wall Pressure Fluctuations Under Separated Supersonic and Hypersonic Flows
Date
1965
Index Abstract
Coming Soon
Photo Quality
Complete
Report Number
AFFDL TR 65-77
Creator
Revell, J. D.
Gleason, R. E.
Corporate Author
Northrop Corporation
Laboratory
Air Force Flight Dynamics Laboratory
Extent
450
Identifier
AD0622395
Access Rights
Notice(s)
Distribution Classification
1
Contract
AF 33(657)-11712
DoD Project
1471
DoD Task
147102
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
Abstract
The objective of the project was to conduct an exploratory theoretical and limited experimental program to obtain the parameters that are important in the occurrence, magnitude, frequency content, and effective areas of forcing functions arising from separated flow, wakes, base pressure fluctuations, and oscillating shock waves. Two models were used to obtain pressure fluctuation data generated by the above mentioned phenomena from wind tunnel tests. These models were purposely constructed to generate separated flows, oscillating shock waves, and base pressure fluctuations. The fluctuating pressure data obtained during the tests were reduced in the form of one-third octave band spectra. These reduced data are compiled. Analyses of these data were made, and are given. Comparisons were made of the effects of Mach number, angle of attack, frequency, and Strouhal number on the sound pressure levels generated.
Report Availability
Full text available
Date Issued
1965-08
Provenance
Lockheed Martin Missiles & Fire Control
Type
report
Format
1 online resource
Media
AFFDLTR65-077.pdf