Accession Number : AD0622395
Title : TURBULENT WALL PRESSURE FLUCTUATIONS UNDER SEPARATED SUPERSONIC AND HYPERSONIC FLOWS.
Descriptive Note : Final technical rept. for 13 Jun 63-1 Mar 65,
Corporate Author : NORTHROP CORP HAWTHORNE CALIF NORAIR DIV
Personal Author(s) : Revell,J. D. ; Gleason,R. E.
Report Date : AUG 1965
Pagination or Media Count : 449
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. (Author)
Descriptors : (*SUPERSONIC FLOW, TURBULENCE), (*TURBULENCE, PRESSURE), ANALYSIS OF VARIANCE, SEPARATION, HYPERSONIC FLOW, STRUCTURES, AERODYNAMIC LOADING, AEROSPACE CRAFT, REENTRY VEHICLES, COMPRESSIBLE FLOW, MODEL TESTS, SHOCK WAVES, OSCILLATION, BASE FLOW
Distribution Statement : APPROVED FOR PUBLIC RELEASE