Turbulent Wall Pressure Fluctuations Under Separated Supersonic and Hypersonic Flows
Report Number: AFFDL TR 65-77
Author(s): Revell, J. D., Gleason, R. E.
Corporate Author(s): Northrop Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-08
Pages: 450
Contract: AF 33(657)-11712
DoD Project: 1471
DoD Task: 147102
Identifier: AD0622395
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.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Revell, J. D., Gleason, R. E.
Corporate Author(s): Northrop Corporation
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1965-08
Pages: 450
Contract: AF 33(657)-11712
DoD Project: 1471
DoD Task: 147102
Identifier: AD0622395
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.
Provenance: Lockheed Martin Missiles & Fire Control