Karnick, Pradeep T and Venkatraman, K (2012) Shock-boundary layer interaction and transonic flutter. In: 65th Annual Meeting of the APS Division of Fluid Dynamics, November 18–20, 2012, San Diego, California.Full text not available from this repository. (Request a copy)
The transonic flutter dip of an aeroelastic system is primarily caused by compressibility of the flowing fluid. Viscous effects are not dominant in the pre-transonic dip region. In fact, an Euler solver can predict this flutter boundary with considerable accuracy. However with an increase in Mach number the shock moves towards the trailing edge causing shock induced separation. This shock-boundary layer interaction changes the flutter boundary in the transonic and post-transonic dip region significantly. We discuss the effect of viscosity in changing the flutter boundary in the post-transonic dip region using a RANS solver coupled to a two-degree of freedom model of the structural dynamics of a wing.
|Item Type:||Conference Paper|
|Additional Information:||Copyright of this article belongs to American Physical Society.|
|Department/Centre:||Division of Mechanical Sciences > Aerospace Engineering (Formerly, Aeronautical Engineering)|
|Date Deposited:||07 Mar 2014 07:17|
|Last Modified:||07 Mar 2014 07:17|
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