Experimental study of crossflow instability on a mach 6 yawed cone

Stuart A. Craig, William S. Saric

Research output: Chapter in Book/Report/Conference proceedingConference contribution

6 Scopus citations

Abstract

The crossflow instability is studied in the boundary layer on a yawed, 7° cone at 5.6° angle of incidence. Experiments are conducted in the Mach 6 Quiet Tunnel at Texas A&M University using constant temperature hot-wire anemometry at Re' = 10 x 106 m1 with an adiabatic wall. Two-dimensional contours of mass flux are measured at a series of axial locations along the cone. Stationary crossflow waves are observed to dominate the flow field and reach saturation. Evidence of traveling waves are also observed to be increasingly confined to the regions between stationary vortices. Secondary instability is observed to arise along the leeward edges of the vortices and exhibits slow growth and saturation-like behavior. Transition was not observed on the model.

Original languageEnglish (US)
Title of host publication45th AIAA Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103629
Publication statusPublished - Jan 1 2015
Externally publishedYes
Event45th AIAA Fluid Dynamics Conference, 2015 - Dallas, United States
Duration: Jun 22 2015Jun 26 2015

Publication series

Name45th AIAA Fluid Dynamics Conference

Other

Other45th AIAA Fluid Dynamics Conference, 2015
CountryUnited States
CityDallas
Period6/22/156/26/15

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ASJC Scopus subject areas

  • Engineering (miscellaneous)
  • Aerospace Engineering

Cite this

Craig, S. A., & Saric, W. S. (2015). Experimental study of crossflow instability on a mach 6 yawed cone. In 45th AIAA Fluid Dynamics Conference (45th AIAA Fluid Dynamics Conference). American Institute of Aeronautics and Astronautics Inc, AIAA.