Influence of Control Mechanism on the Flow field of Duct at Mach 1.2 for Area Ratio 2.56
S. A. Khan1, Abdul Aabid2, Zakir Ilahi Chaudhary3
1S. A. Khan, Department of Mechanical Engineering Faculty of Engineering, International Islamic University, Kuala Lumpur, Malaysia.
2Abdul Aabid, Department of Mechanical Engineering Faculty of Engineering, International Islamic University, Kuala Lumpur, Malaysia.
3Zakir Ilahi Chaudhary, Department of Automobile Engineering, Mental Health Support Solutions College of Engineering, Mumbai, India.
Manuscript received on 13 April 2019 | Revised Manuscript received on 20 April 2019 | Manuscript Published on 26 July 2019 | PP: 1135-1138 | Volume-8 Issue-6S4 April 2019 | Retrieval Number: F12360486S419/19©BEIESP | DOI: 10.35940/ijitee.F1236.0486S419
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© The Authors. Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP). This is an open-access article under the CC-BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/)
Abstract: In this paper, the outcome of the experimental investigation and the flow field development in the duct at supersonic Mach number of 1.2 is presented. The experiments were conducted at various NPR which covers the condition of correct expansion and under expansion. A Convergent-divergent (C-D) nozzle which is connected with the suddenly expanded duct of the diameter of 16 mm of area ratio 2.56. The recirculation zone is controlled by using the microjets of 1 mm of orifice diameter which are placed at 90 degrees interval at 6.5 mm from the central axis of the main jet. The L/D of the duct was used in the investigation was from 1 to 10, and the NPR at which the experiments were conducted considered are in the range from 3, 5, 7, 9 and 11.
Keywords: CD Nozzle; Microjet; Wall Pressure; and Mach number.
Scope of the Article: Mechanical Maintenance