Wall pressure fluctuations beneath swept shock wave/boundary layer interactionsAn experimental research program providing basic knowledge and establishing a database on the fluctuating pressure loads produced on aerodynamic surfaces beneath 3D shock wave/boundary layer interactions is presented. A turbulent boundary layer on a flat plate is subjected to interactions with swept planar shock waves generated by sharp fins at angle of attack. Measurements are made for the first time in the aft areas of these interactions, showing fluctuating pressure levels as high as 160 dB.
Document ID
19930039066
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Garg, S. (NASA Langley Research Center Hampton, VA, United States)
Settles, G. S. (Pennsylvania State Univ. University Park, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 93-0384
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit