Unsteady Transonic Flow Past Airfoils In Rigid Body Motion

Excerpt from Unsteady Transonic Flow Past Airfoils in Rigid Body Motion We begin our discussion with a brief survey of the behavior of flows past airfoils; when a conventional symmetric airfoil accelerates from subsonic speed to supersonic speed the flow pattern usually develops in the manner shown in Figure 11. As the flight speed of the airfoil reaches the critical speed, the local flow speed equals the local sound speed. Beyond the critical speed, a supersonic region appears on the airfoil which is usually terminated by a nearly normal shock through which the flow speed jumps from super sonic to subsonic. With a further increase in the flight speed, the shock moves aft and the size of the supersonic region and the shock strength both increase. If the pressure jump through the shock is sufficiently large, separation of the boundary layer occurs. This shock induced separation starts when the local Mach number, the ratio of local flow and sound speeds, just upstream of the shock is about to When the boundary layer downstream of the shock separates. About the Publisher Forgotten Books publishes hundreds of thousands of rare and classic books. Find more at www.forgottenbooks.com This book is a reproduction of an important historical work. Forgotten Books uses state-of-the-art technology to digitally reconstruct the work, preserving the original format whilst repairing imperfections present in the aged copy. In rare cases, an imperfection in the original, such as a blemish or missing page, may be replicated in our edition. We do, however, repair the vast majority of imperfections successfully; any imperfections that remain are intentionally left to preserve the state of such historical works.

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Mathematics Research Center Symposium: Transonic, Shock, and Multidimensional Flows: Advances in Scientific Computing covers the lectures presented at a Symposium on Transonic, Shock, and Multidimensional Flows, held in Madison on May 13-15, 1981, under the auspices of the Mathematics Research Center of the University of Wisconsin. The book focuses on the advancements in the scientific computation of high-speed aerodynamic phenomena and related fluid motions. The selection first elaborates on computational fluid dynamics of airfoils and wings; shock-free configurations in two- and three-dimensional transonic flow; and steady-state solution of the Euler equations for transonic flow. Discussions focus on boundary conditions, convergence acceleration, indirect design of airfoils, and trailing edge and the boundary layer. The text then examines the calculation of transonic potential flow past three-dimensional configurations and remarks on the numerical solution of Tricomi-type equations. The manuscript ponders on the design and numerical analysis of vortex methods, shock calculations and the numerical solution of singular perturbation problems, tracking of interfaces for fluid flow, and transonic flows with viscous effects. Topics include numerical algorithm, difference approximation for scalar equations, boundary conditions, transonic flow in a tube, and governing equations. The selection is a dependable reference for researchers interested in transonic, shock, and multidimensional flows.