Titlebook: IUTAM Symposium Transsonicum IV; Proceedings of the I H. Sobieczky Conference proceedings 2003 Springer Science+Business Media Dordrecht 20

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New Results for the Normal Shock in Inviscid Flow at a Curved Surface,determinated.We can only prescribe the curvature of the wall in front of the shock and the Machnumber there. The curvature of the streamline behind the shock is not a priori given. The complete solution is discussed. New effects, not unusual in nonlinear gasdynamics, are found.

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Nonlinear Aerodynamic Effects on Transonic LCO Amplitude of a Supercritical Airfoil,e amplitudes of the transonic limit cycle oscillations (LCO) of a supercritical airfoil. As expected, stronger aerodynamic nonlinearity leads to smaller LCO amplitudes, even a damped solution while weaker aerodynamic nonlinearity incurs larger LCO amplitudes, even a divergent solution.

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triptans

On the Effect of Area Ruling on Transonic Abrupt Wing Stall,he pre and post-stall regime are presented, and it is shown that small changes in the cross-sectional area distribution in the aft body has a significant effect on the onset of wing stall, but more systematic computations are needed before the effectiveness of area-ruling can be firmly established.

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,A Unified Variational Formulation of Aero-Elasticity Problem for Coupled ‘Fluid-Wing’ Vibration Sysons in, while removing final-value conditions from the VP is also suggested, eliminating the inherent defect of VP of being unable to properly handle initial-value problems. Thus, a new complete theoretical basis for the aeroelastic analysis of wing vibration (esp. flutter) and response by the finite element method is provided.

Cupping

,Unsteady Transonic Flow Past “Non-Unique” Airfoils,ood of the non-unique regime been considered. The present study investigates the unsteady behavior for transonic flow past one of these airfoils-the Jameson J-78-numerically, using a dual-time stepping (temporally sub-iterated) implicit multigrid scheme [[.]] to solve the unsteady Euler equations.

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inspired

Transonic Solutions for the Mach Reflection of Weak Shocks,riple point resolves the von Neumann paradox. The numerical results and theoretical considerations suggest that there may be an infinite sequence of triple points in an inviscid weak shock Mach reflection.