Estimation of Shock Induced Buffet Onset

Singh, JP (1999) Estimation of Shock Induced Buffet Onset. Technical Report. National Aerospace Laboratories, Bangalore, India.

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Abstract

A code based on the cell-centered explicit finite volume method with Runge-Kutta time13; stepping scheme and acceleration techniques like local time-stepping, implicit residual13; smoothing and multigrid has been used to estimate the . shock-induced buffet onset of13; NACA 0012 airfoil. Such methods are basically meant to compute steady flows. The flow,13; with shock-induced oscillations isc;'totally unsteady phenomenon and its detailed study13; must be made using time-accurate computations. However, if the purpose is just to13; estimate the shock-induced buffet onset, like the information that the aerodynamic design13; engineer may desire to get, it may be enough to estimate the buffet onset boundary13; without getting into the details of its time-accurate nature. This estimation is obtained in a far too lesser computational time as the code is highly accelerated. Estimate of an13; important aerodynamic parameter such as this, obtained so quickly, is of great help to the13; aerodynamic engineer. The justification to use a steady state code to compute an13; unsteady flow phenomenon is that a basically unsteady flow will remain unsteady and its nature is not altered by using steady state method. The basic information related to the13; time accurate history will, of course, not be available.

Item Type:	Proj.Doc/Technical Report (Technical Report)
Uncontrolled Keywords:	Buffet Onset;Navier-Stokes solutions.
Subjects:	AERONAUTICS > Aircraft Design, Testing & Performance
Division/Department:	Flosolver Division
Depositing User:	Mrs Manoranjitha M D
Date Deposited:	08 May 2006
Last Modified:	24 May 2010 09:41
URI:	http://nal-ir.nal.res.in/id/eprint/1243

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