Accession Number : ADA582401


Title :   Measurements in Regions of Shock Wave/Turbulent Boundary Layer Interaction from Mach 3 to 10 for Open and Blind Code Evaluation/Validation


Descriptive Note : Final rept. Sep 2011-Sep 2012


Corporate Author : CUBRC INC BUFFALO NY


Personal Author(s) : Holden, Michael S ; Wadhams, Timothy P ; MacLean, Matthew G ; Dufrene, Aaron


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a582401.pdf


Report Date : Mar 2013


Pagination or Media Count : 28


Abstract : Experimental studies have been conducted to examine the characteristics of regions of shock wave/turbulent boundary layer interaction over cone/flare and hollow cylinder/flare configurations in high Reynolds number flows at Mach numbers between 5 and 10 in cold flows and in flows with duplicated flight velocities. Detailed surface pressure and heat transfer measurements have been made through the separated interaction regions as well as upstream and downstream of the interactions for a range of Reynolds numbers under cold wall conditions for total enthalpies duplicating flight. The large scale of the models used in these experiments enabled us to obtain measurements in fully turbulent flows with the length of turbulent flow up to 1,000 boundary layer thicknesses downstream of the beginning of untripped transition. The surface measurements obtained in these studies together with Schlieren and interferometry measurements of the regions of shock wave/boundary layer interaction have been assembled to provide data sets for blind code validation studies.


Descriptors :   *INTERACTIONS , *SHOCK WAVES , *TURBULENT BOUNDARY LAYER , ENTHALPY , FLIGHT , FLOW SEPARATION , HEAT TRANSFER , HYPERSONIC FLOW , REYNOLDS NUMBER , SUPERSONIC FLOW , TURBULENT FLOW


Subject Categories : Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE