We establish the existence of the viscous proole of an undriven divergent detonation wave for a model problem with small viscosity. It is known that there is a sonic point inside the reaction zone of a divergent detonation wave. As a consequence, the detonation wave proole is a transonic proole and the wave speed cannot be determined before the problem is solved. The wave speed may be interpret...

In this paper we construct a class of transonic shock in a divergent nozzle which is a part of an angular sector (for two-dimensional case) or a cone (for three-dimensional case) which does not contain the vertex. The state of the compressible flow depends only on the distance from the vertex of the angular sector or the cone. It is supersonic at the entrance, while for appropriately given larg...

The paper investigates the application of two advanced optimisation methods for solving active flow control device shape design problem and compares their optimisation efficiency in terms of computational cost and design quality. The first optimisation method uses Hierarchical Asynchronous Parallel Multi-Objective Evolutionary Algorithm (HAPMOEA) and the second uses Hybridized EA with Nash-Game...

Using certain finite-dimensional stable range of the nonlinear terms, we obtain large families of exact solutions parameterized by functions for the equation of nonstationary transonic gas flows discovered by Lin, Reisner and Tsien, and its three-dimensional generalization.

This paper discusses the use of control theory for optimum design of aerodynamic configurations. Examples are presented of the application of this msethod to the reduction of shock induced pressure drag on airfoils in two-dimensional transonic flow.

available at: https://www.grc.nasa.gov/hiocfd/workshop-results/ Case C1.2b: Flow over the NACA0012 airfoil transonic case Andrea Ferrero∗and Francesco Larocca† Department of Mechanical and Aerospace Engineering Politecnico di Torino, Italy