Transonic vortical gas flows
Author(s)
Bibliographic Information
Transonic vortical gas flows
John Wiley, c1994
Available at / 10 libraries
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Hokkaido University, Library, Graduate School of Science, Faculty of Science and School of Science図書
629.132/SH612070390526
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Description and Table of Contents
Description
A flow becomes vortical because of rising shock waves which lead to loss of energy in supersonic zones. This study combines analytical and numerical approaches to solve actual problems in transonic aerodynamics which can be applied, for instance, to the supercritical flow around an airplane of a stream with a high subsonic velocity. Following the trend of current applied science and improving the accuracy of calculations, the text presents general analysis investigations of the structure and properties of typical transonic flows with the relevant numerical solutions. The study also addresses the general mathematical concept based on the Chaplygin hodograph method, the current state of theory and applications for the Laval Nozzle, flows over a profile or a corner point, and axysymmetric transonic flows.
Table of Contents
- General Properties of Transonic Flows of an Ideal Gas
- A Flow in a Vicinity of the Orthogonality Point of the Sonic Line to the Velocity Vector
- The Laval Nozzle: Problems and Theoretical Investigation
- The Laval Nozzle: Numerical Methods for Solving Profiling and Direct Problems
- A Subcritical Flow Over a Profile
- A Supercritical Flow Over a Profile
- A Transonic Flow Over a Corner Point
- A Transonic Flow Behind a Detached Shock Wave in a Supersonic Gas Flow About a Body
- Secondary Shocks
- A Uniform Jet Flow Over a Profile
- Axisymmetric Transonic Flows.
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