Numerical Calculation Of The Transonic Flow Past A Swept Wing

NUMERICAL CALCULATION OF THE TRANSONIC FLOW PAST A SWEPT WING

Numerical Calculation of the Transonic Flow Past a Swept Wing (Classic Reprint)

Excerpt from Numerical Calculation of the Transonic Flow Past a Swept Wing The development of profile shapes capable of efficient operation in the transonic regime has spurred interest in flight vehicles designed specifically to Operate at near sonic speeds. The ability to predict accurately the aerodynamic characteristics of the complete three-dimensional wing should have a substantial impact on the design of such vehicles by allowing detailed trade off studies to be performed without recourse to wind tunnel test ing of every design variation. 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.

Numerical Calculation of Transonic Flow Past a Swept Wing by a Finite Volume Method

The finite volume method for the numerical calculation of transonic flow past a swept wing was developed and its use for calculating the pressure distribution on the upper surface of a Onera m6 wing in Mach No. 0.84 flow and of a Douglas DC10 wing in M = 0.85 flow is illustrated. Calculated results are compared with experimental data. The results confirm the promise of the new method. It appears that it can be used to treat configurations of more or less arbitrary complexity, subject to limits set by the power of the available computers. The extension to new configurations is primarily a matter of devising mesh generating schemes, since the internal computations are essentially independent of the configuration, apart from the identification of which elements are the boundary elements. (LCL).