Proceedings of the Special Course on Missile Aerodynamics, Held in Rhode-Saint-Genese, Belgium on 30 March-3 April 1987, Held in Athens, Greece on 18-19 May 1987 Held in Ankara, Turkey on 21-22 May 1987 PDF Download

Author: ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)
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Languages : en
Pages : 475

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Book Description
This course of 12 lectures presents the current state of the art in fundamental knowledge and in practical predictive methods in tactical missile aerodynamics. The first lecture surveys aerodynamic problems encountered on existing and future missiles and the most important predictive methods. A lecture follows on the criteria that define the required prediction accuracy in terms of allowable errors in missile performance and design parameters. The 3rd lecture covers nonlinear aerodynamic effects including formation of flow separation vortices, vortex wakes and vortical interference, and nonlinear compressibility due to presence of shocks. Several lectures present engineering computation methods used for calculating stability and control for conventional and unconventional missiles, illustrated by numerous practical examples. They fall into two categories: semi-empirical methods based on the equivalent angle-of-attack concept and numerical methods, much more recent, based on the resolution of the steady and the unsteady Euler equations with flow separation vortices. Prediction of dynamic derivatives is also presented with a description of the experimental methods. An extensive lecture describes the role of the intake in the propulsion system of turbojet and ramjet powered missiles and addresses both the internal and external aerodynamic aspects of the induction system. A computer aided design procedure for use in conceptual design for sizing and shaping supersonic airbreathing missiles is presented. The prediction of aerodynamic heating and base flows with and without propulsion, and the design of the next generation supersonic and hypersonic missiles are discussed. (edc).