Micro-Ramp Flow Control for Oblique Shock Interactions : Comparisons of Computational and Experimental Data

Author:: O'Connor, Michael B.
Published:: August 2012.
Physical Description:: 1 electronic document
Additional Creators:: Reich, David B. and Hirt, Stephanie M.

Online Version

hdl.handle.net , Connect to this object online.

Availability

Finding items...

Restrictions on Access:

Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access

Summary:

Computational 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.

Other Subject(s):

Aerodynamics

Collection:

NASA Technical Reports Server (NTRS) Collection.

Note:

Document ID: 20120013216.
AIAA Paper 2010-4973.
NASA/TM-2012-217242.
E-17976-1.

Terms of Use and Reproduction:

View MARC record | catkey: 15978339