Accession Number : ADA268394


Title :   An Experimental Study of Fluctuating Wall Pressures in a Highly Swept, Sharp Fin-Induced, Mach 5 Shock Wave/Turbulent


Descriptive Note : Final rept. Aug 90-May 92,


Corporate Author : WRIGHT LAB WRIGHT-PATTERSON AFB OH


Personal Author(s) : Schmisseur, J D


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a268394.pdf


Report Date : Jan 1993


Pagination or Media Count : 150


Abstract : Fluctuating wall pressure measurements have been made beneath the shock wave/turbulent boundary layer interaction generated by a sharp, unswept fin at angle of attack. Tests were conducted at Mach 5 with a freestream unit Reynolds number of 47.88 x 106 /m. The boundary layer developed naturally on the tunnel floor under approximately adiabatic temperature conditions. From visual inspection and standard time series analysis of fluctuating wall pressure signals, it has been shown that the separation shock wave undergoes a translating, intermittent type motion for fin angles between 16 and 28 degrees. Both the mean wall pressures and higher order moments are quasi-conically symmetric when collapsed in a conical coordinate system. Finally, the maximum wall pressure standard deviation in the intermittent region has been shown to scale with the sweep of the interaction and not with the inviscid pressure rise as has been previously suggested in the literature.... Shock wave, Boundary layer, Turbulent interaction, Interaction unsteadiness.


Descriptors :   *SHOCK WAVES , *TURBULENT BOUNDARY LAYER , *PRESSURE , *FINS , *HYPERSONIC FLIGHT , TEST AND EVALUATION , TEMPERATURE , MOTION , COMPUTATIONAL FLUID DYNAMICS , FLOW FIELDS , VISUAL INSPECTION , REYNOLDS NUMBER , STANDARD DEVIATION , LAMINAR FLOW , FLOW SEPARATION , MACH NUMBER , WALLS , COORDINATES , ANGLE OF ATTACK , BOUNDARY LAYER , THESES , TIME SERIES ANALYSIS , INTERACTIONS


Subject Categories : Aerodynamics


Distribution Statement : APPROVED FOR PUBLIC RELEASE