Unsteady Aspects of Shock-Wave/Boundary-Layer Interaction Resulting from Control Surface Deflection

A computational investigation of a Mach 6.9 turbulent flow near the juncture (cove) of a wing’s trailing-edge and elevon was carried out. Turbulence was modeled using improved delayed detached eddy simulation (IDDES). The computational data were compared to the results of an experimental study, cond...

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Bibliographic Details
Published in:AIAA journal 2022-08, Vol.60 (8), p.4649-4659
Main Authors: Alviani, Robert, Poggie, Jonathan, Blaisdell, Gregory
Format: Article
Language:English
Subjects:
Aeronautics
Boundary conditions
Boundary layer interaction
Control surfaces
Correlation analysis
Detached eddy simulation
Flow control
Flow simulation
Flow visualization
Geometry
Heat flux
Pressure
Reynolds number
Shear layers
Shock wave interaction
Simulation
Software
Turbulence
Unsteady flow
Visualization
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Summary:A computational investigation of a Mach 6.9 turbulent flow near the juncture (cove) of a wing’s trailing-edge and elevon was carried out. Turbulence was modeled using improved delayed detached eddy simulation (IDDES). The computational data were compared to the results of an experimental study, conducted by Deveikis and Bartlett, which simulated the flow over the windward surface of the NASA space shuttle. Flow visualization, surface variable comparison with experiment, and analysis of unsteady flow statistics were carried out. Reasonable agreement between prediction and measurement was obtained for time-averaged surface pressure and heat flux. Unsteady analysis of these quantities revealed spectra dominated by low-frequency energy content throughout the interaction region. A correlation analysis indicated coupling of the unsteady motions of the shear layer, shock wave, separation vortex, and flow reattachment. The results of the present study suggest that IDDES can be a valuable tool for the analysis of heating and unsteadiness in hypersonic gap flows.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J061337