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Paper Information

Title: 

INVESTIGATION OF CORNER ROUNDING EFFECTS ON THE PERFORMANCE OF A SUPERSONIC AIR INTAKE

Type: PAPER
Author(s): SEPAHI YOUNSI JAVAD*,FOROUZI FESHALAMI BEHZAD
 
 *MECHANICAL ENGINEERING DEPARTMENT, FACULTY OF ENGINEERING, FERDOWSI UNIVERSITY OF MASHHAD, MASHHAD, IRAN
 
Name of Seminar: CONFERENCE OF IRANIAN AEROSPACE SOCIETY
Type of Seminar:  CONFERENCE
Sponsor:  IRANIAN AEROSPACE SOCIETY
Date:  2017Volume 16
 
 
Abstract: 

IN THIS RESEARCH, FLOW IS SIMULATED NUMERICALLY THROUGH AND AROUND A MIXED-COMPRESSION INTAKE TO INVESTIGATE EFFECTS OF CORNER ROUNDING ON INTAKE PERFORMANCE AT FREE STREAM MACH NUMBERS OF 1.8, 2 AND 2.2 AND AT ZERO DEGREES ANGLE OF ATTACK. FURTHERMORE, EFFECTS OF DIFFERENT MACH NUMBERS AND BACK PRESSURES ARE STUDIED. TOTAL PRESSURE RECOVERY (TPR), FLOW DISTORTION (FD), MASS FLOW RATIO (MFR), AND DRAG COEFFICIENT (CD), ARE CHOSEN AS THE INTAKE PERFORMANCE PARAMETERS. CFD RESULTS ARE VALIDATED WITH EXPERIMENTAL DATA. RESULTS SHOWED THAT INCREMENT OF BACK PRESSURE GENERALLY CAN IMPROVE THE PERFORMANCE WHILE INCREASING MACH NUMBER HAS UNFAVORABLE EFFECTS ON TPR. ALSO APPLYING FILLET CAN SIGNIFICANTLY IMPROVE PERFORMANCE PARAMETERS OF FD AND MFR. HOWEVER IT DOESN'T TPR AND CD.

 
Keyword(s): SUPERSONIC INTAKE, INTAKE PERFORMANCE, FILLET RADIUS OF CURVATURE, MACH NUMBER
 
 
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