IIUM Repository (IREP)

Effect of mach number on wall pressure flow field for area ratio 2.56

Ashfaq, Syed and Khan, Sher Afghan (2014) Effect of mach number on wall pressure flow field for area ratio 2.56. IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE), 11 (2). pp. 56-64. ISSN 2320-334X

[img] PDF - Published Version
Restricted to Repository staff only

Download (1MB) | Request a copy

Abstract

This paper presents the experimental results on the flow characteristics of a suddenly expanded flow from the convergent nozzle for subsonic flow. In the present study micro jets were used to investigate the effect of micro jets on wall pressure flow field in the enlarged duct. Accordingly an active control in the form of four micro jets of 1 mm orifice diameter located at 900 intervals along a pitch circle diameter of 1.3 times the nozzle exit diameter in the base region was employed. The Mach numbers of the present studies were M = 0.9, 0.8, and 0.6 and the area ratio (ratio of area of suddenly expanded duct to nozzle exit area) studied was 2.56. The length-to-diameter (i.e. L/D) ratio of the sudden expansion duct was varied from 10 to 1. From the results, it is seen that the flow in the base region is dominated by the waves, the general perception what we have that correctly expanded flow will be from waves is proved to be wrong; also, it is found that for L/D in the range L/D = 10 and 8 the flow remains oscillatory mostly for all the Mach numbers. However, these oscillations are suppressed gradually either with the increase in the L/D ratio in the range 3 to 6 or with decrease in the level of inertia level. The present study explicitly reveals that, the wall pressure in a suddenly expanded axi-symmetric duct can be controlled by employing micro jets. Since the flow field in the enlarged duct remained undisturbed hence, we can say that the control in the form of micro jets don’t disturb the field.

Item Type: Article (Journal)
Additional Information: 7395/49919
Uncontrolled Keywords: Active control, Area ratio, Base pressure, L/D ratio, Micro jets, Static wall pressure
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500 Aeronautics
Kulliyyahs/Centres/Divisions/Institutes: Kulliyyah of Engineering > Department of Mechanical Engineering
Depositing User: Prof. Dr. Sher Afghan Khan
Date Deposited: 11 Apr 2016 09:18
Last Modified: 20 Jun 2018 14:42
URI: http://irep.iium.edu.my/id/eprint/49919

Actions (login required)

View Item View Item

Downloads

Downloads per month over past year