Performance Optimization of an Axisymmetric Supersonic Inlet

Please enable javascript in your browser.

Mahdavi, Mohammad Mahdi | 2018

393 Viewed

Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 51370 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Farahani, Mohammad
Abstract:
The main aim of this study is to propose a new structure of compression surfaces of a supersonic inlet in order to improve target performance parameter i.e. total pressure recovery ratio. This idea resulted in developing a new type of supersonic inlet, utilizing four ramps and a cone as compression surfaces simultaneously.A prototype of this type of inlet has been designed for Mach 3 and its performance has been studied via numerical simulation in design point and off design conditions. Eventually the new inlet compared to experimental performance survey data from two cases of two-cone inlets and also analytical calculations of ideal performance of some types of supersonic inlets. Results of comparisons confirms the effectiveness of main idea of this thesis.Total pressure recovery ratio of designed inlet at its design point condition is 76.8 %
Keywords:
Inlet ; Supersonic Flow ; Optimization ; Shock Wave ; Shock Waves Structure

No TOC