Journal of Engineering Research
Salaheldin Omar, Salem Abossmait
Abstract
In this wind-tunnel investigation, unsteady 3-D velocity components over a hypersonic delta glider have been measured in subsonic wind tunnel using a constant temperature hot-wire probe at different angles of attack. The effect of the intrusive hotwire probe on the vortex core and the vortex structure has been predicted at angles of attack over 25 degree and x/Cr=0.9 resulting in an early vortex breakdown. Stream wise, vertical and lateral root-mean-square velocity components over the wing have been presented. The acquired data are correlated to the surface-pressure data and the laserlight-sheet results published by the author.
Topics & Concepts
Computer scienceEngineering ethicsData scienceEngineeringComputational Fluid Dynamics and AerodynamicsFluid Dynamics and Turbulent FlowsAerodynamics and Acoustics in Jet Flows