NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Micro-Ramp Flow Control for Oblique Shock Interactions: Comparisons of Computational and Experimental DataComputational fluid dynamics was used to study the effectiveness of micro-ramp vortex generators to control oblique shock boundary layer interactions. Simulations were based on experiments previously conducted in the 15- by 15-cm supersonic wind tunnel at the NASA Glenn Research Center. Four micro-ramp geometries were tested at Mach 2.0 varying the height, chord length, and spanwise spacing between micro-ramps. The overall flow field was examined. Additionally, key parameters such as boundary-layer displacement thickness, momentum thickness and incompressible shape factor were also examined. The computational results predicted the effects of the microramps well, including the trends for the impact that the devices had on the shock boundary layer interaction. However, computing the shock boundary layer interaction itself proved to be problematic since the calculations predicted more pronounced adverse effects on the boundary layer due to the shock than were seen in the experiment.
Document ID
20120013216
Document Type
Technical Memorandum (TM)
Authors
Hirt, Stephanie M.
(NASA Glenn Research Center Cleveland, OH, United States)
Reich, David B.
(Florida Univ. Gainesville, FL, United States)
O'Connor, Michael B.
(Notre Dame Univ. Notre Dame, IN, United States)
Date Acquired
August 26, 2013
Publication Date
August 1, 2012
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2012-217242
E-17976-1
AIAA Paper 2010-4973
Funding Number(s)
WBS: WBS 984754.02.07.03.13.02
Distribution Limits
Public
Copyright
Public Use Permitted.

Available Downloads

NameType 20120013216.pdf STI
No Preview Available