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Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD

Quadros, Jaimon Dennis and Khan, Sher Afghan and A. J., Antony and Vas, Jolene S. (2016) Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD. In: International Conference on Energy Systems and Developments (ICESD2016), 19th-20th Feb. 2016, Pune, India.

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Abstract

Researches over the recent past in the field of aerodynamic vehicles have been concerned with the problem of flow separation over its base which has lead to the formation of low pressure circulation region. This pressure is found to be noticeably lower than the free stream atmospheric pressure. Base drag due to such pressure differences can be up to twothirds of the total drag and is principally dictated by base pressure. The present study aims to conduct experiments in order to study the variation of base pressure from an axisymmetric nozzle exit of 10mm diameter. Area ratio i.e. ratio of area of suddenly expanded duct to nozzle exit area considered in this particular study is 4.84. The fundamental control parameters considered in the study are the nozzle pressure ratio (NPR) and length-to-diameter (L/D) ratio which apparently are the inertia and geometric parameters respectively. The tests are conducted for NPR’s ranging from 3 to 11 in steps of 2. Accordingly L/D ratio was considered from 10 to 1 where tests were conducted for L/D 10, 9, 8, 7, 6, 5, 4, 3, 2 and 1. The results showed that for increase in the NPR values once the flow is attached to the duct, the base pressure progressively decreased. Wall pressure distribution throughout the enlarged duct is also studied to understand the oscillatory nature of flow. This work also proposes an effective numerical model for base pressure using Computational Fluid Dynamics (CFD). The computational/numerical model of the axisymmetric nozzle and the enlarged duct was constructed using ANSYS Fluent which is the CFD solver and employed in the present work. Numerical iterations were completed, and the detailed values for base pressure are analyzed. The numerical results were found to agree well with the experimental ones.

Item Type: Conference or Workshop Item (Plenary Papers)
Additional Information: 7395/51127
Uncontrolled Keywords: axisymmetric nozzle flow, Mach 3.0, CFD
Subjects: T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL500 Aeronautics
T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL780 Rockets
T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL787 Astronautics
Kulliyyahs/Centres/Divisions/Institutes: Kulliyyah of Engineering > Department of Mechanical Engineering
Depositing User: Prof. Dr. Sher Afghan Khan
Date Deposited: 01 Aug 2016 16:57
Last Modified: 12 Oct 2017 20:38
URI: http://irep.iium.edu.my/id/eprint/51127

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