Paper Information

Journal:   MODARES MECHANICAL ENGINEERING   FEBRUARY 2017 , Volume 16 , Number 11 #F0072; Page(s) 303 To 310.
 
Paper: 

DESIGN OF SUPERSONIC INLET BASED ON SHOCK WAVE

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

Integration of airframe and propulsion system is one of the most challenging steps in flight vehicle design cycles. In this paper, a three-dimensional supersonic inlet based on the wave-derived geometry technique has been designed and analyzed. Although the considered method was created for hypersonic forebodies, the idea is fully operational for the low supersonic inlet design at Mach 1.6. The inlet concept in this paper is formed from predefined profile elements which are used to generate the threedimensional geometry in an oblique shock pattern. By this approach, the curved corner of the inlet entrance edge can generate the same shock as the main compression surface and also these curved surfaces provide the optimum transition between entrance geometry and compressor face which is important for the airflow quality and propulsive efficiency. The new concept has been validated by a series of accurate CFD simulations with completely structural grid domains. The major inlet' s performance factors like total pressure recovery, flow distortion and mass flow capture ratio are calculated. The concept and its accurate numerical simulations create a baseline for more advanced designs and researches about the three-dimensional inlets and geometry transition techniques between the different sections of duct.

 
Keyword(s): THREE DIMENSIONAL SUPERSONIC INLET, WAVE-DERIVED GEOMETRY, NUMERICAL SIMULATION, AIRBREATHING PROPULSION, SUBSONIC DIFFUSER
 
References: 
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