Studies on Flows Development in a Suddenly Expanded Circular Duct at Supersonic Mach Numbers

نویسندگان

چکیده

This article focuses on the flow development and static wall pressure distribution along circular duct from convergent-divergent (CD) nozzle. The study aims to examine quality of stream in conduit when control is employed. microjets are activated at base (PCD) 13 mm, diameter 1 mm. Mach numbers investigation 1.3, 1.9, 2.4. length considered was L = 10D 1D. enlarged tube 16 experiments were conducted for NPRs 3 11. results revealed that lowest mandatory continued attach with L/D 1, 2, 2.4, respectively. outcome indicates there mild oscillations flow-field correctly expanded flows. oscillatory trend has a pronounced impact duct's jets operated higher NPRs. does not adversely affect field, magnitude nearly similar.

برای دانلود رایگان متن کامل این مقاله و بیش از 32 میلیون مقاله دیگر ابتدا ثبت نام کنید

اگر عضو سایت هستید لطفا وارد حساب کاربری خود شوید

منابع مشابه

Modelling of Suddenly Expanded Flow Process in Supersonic Mach Regime using Design of Experiments and Response Surface Methodology

The present work is an attempt to model, analyze, and control the flow at the base of an abruptly expanded circular duct by using design of experiments (DOE) and response surface methodology (RSM). Tiny-jets in the form of orifice were positioned at an interval of 900, 6.5 mm from the primary axis of the main jet of the nozzle. Experiments were conducted to measure two responses namely, base pr...

متن کامل

A preconditioned solver for sharp resolution of multiphase flows at all Mach numbers

A preconditioned five-equation two-phase model coupled with an interface sharpening technique is introduced for simulation of a wide range of multiphase flows with both high and low Mach regimes. Harten-Lax-van Leer-Contact (HLLC) Riemann solver is implemented for solving the discretized equations while tangent of hyperbola for interface capturing (THINC) interface sharpening method is applied ...

متن کامل

Control of Nozzle Flow Using Microjets at Supersonic Mach Regime

This article reports the active control of base flows using the experimental procedure. Active control of base pressure helps in reducing the base drag in aerodynamic devices having suddenly expanded flows. Active control in the form of microjets having 0.5 mm radius placed at forty-five degrees apart is employed to control the base pressure. The Mach numbers of the present analysis are 1.7, 2....

متن کامل

Vortex Flows at Supersonic Speeds

...............................................................................................................................................................

متن کامل

Control of Nozzle Flow in Suddenly Expanded Duct with Micro Jets

This paper presents results of an experimental investigation carried out to control the base pressure in a suddenly expanded axisymmetric passage. Four micro-jets of 1 mm orifice diameter located at 90 0 intervals along a pitch circle diameter of 1.3 times the nozzle exit diameter in the base region were employed as active controls. The tests were conducted for Mach numbers 1.25, 1.3, 1.48, 1.6...

متن کامل

ذخیره در منابع من


  با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید

ژورنال

عنوان ژورنال: International Journal of Heat and Technology

سال: 2021

ISSN: ['0392-8764']

DOI: https://doi.org/10.18280/ijht.390120