Paper Information

Journal:   MODARES MECHANICAL ENGINEERING   JULY 2017 , Volume 17 , Number 4 #P0099; Page(s) 199 To 208.
 
Paper: 

DESIGN AND NUMERICAL ANALYSIS OF MACH 3.0 INLET

 
Author(s):  BONDAR SAHEBY EIMAN, OLYAEI GHADER, KEBRIAEE AZADEH*
 
* DEPARTMENT OF AEROSPACE ENGINEERING, SHARIF UNIVERSITY OF TECHNOLOGY, TEHRAN, IRAN
 
Abstract: 

Planar inlet concepts play an important role in the design of supersonic propulsion systems. The inlet reduces the speed of supersonic flow by the oblique shock wave or an array of oblique shock waves and a final normal shock provides the subsonic flow after the throat of the diffuser. In this paper, a design method of Mach 3.0 supersonic multi-ramp inlet is explained; the geometry is designed and simulated by the numerical solver. Designing the inlets for the high supersonic Mach range between 3 and 5 is very challenging because of the viscosity interactions and the related effects on the propulsive efficiency. The considered inlet in this study is a mixed system which provides the required compression by a combination of the three external ramps and a subsonic diffuser. A computational code calculated the optimum dimensions numerically and a second order CFD solver has simulated the inlet operations with an accuracy of 10E-05. In addition to aerodynamic performance, advantages and challenges of such a combination, development of boundary layer and its interactions with the normal shock and performance of bleeding mechanism are simulated and studied. Finally, this paper presents compact details of design, simulation and viscosity effect of mixed compression surface.

 
Keyword(s): SUPERSONIC MIX COMPRESSION SYSTEM, MULTIRAMP INLET, AIRBREATHING PROPULSION, NUMERICAL SIMULATION, BOUNDARY LAYER EFFECTS
 
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