Supersonic Streamwise Corner Flows
Abstract
The objective of this research is to improve the understanding of supersonic corner flows and shock-induced corner separations so that numerical prediction methods and future vehicle designs can take proper account of this important phenomenon. The specific aims of the research are:- Provide reference data for supersonic stream-wise corner flows (in the absence of pressure gradients).- Identify the key flow structures of supersonic corner flows and their dependence on various parameters (such as prior boundary layer history).- Provide reference data for separated corner flows and identify the key physics of shock-induced corner separations.- Explore flow control methodologies specific to corner flows.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Dec 05, 2016
- Source ID
- FA95501610430
Entities
People
- Holger Babinsky
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Cambridge