Control of suddenly expanded flow

QR Code

Control of suddenly expanded flow

This paper presents an experimental investigation to study the effectiveness of micro jets under the influence of Over, Under, and Correct expansion to control the base pressure in suddenly expanded axi‐symmetric ducts.Four micro jets of 1 mm orifice diameter located at 90° intervals along a pitch c...

Full description

Bibliographic Details
Main Authors:	Khan, Sher Afghan, Rathakrishnan, E.
Format:	Article
Language:	English
Published:	Emerald Group Publishing 2006
Subjects:	TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets
Online Access:	http://irep.iium.edu.my/46704/ http://irep.iium.edu.my/46704/3/Control_of_suddenly_expanded_flow.pdf

Similar Items

Nozzle expansion level effect on a suddenly expanded flow
by: Khan, Sher Afghan, et al.
Published: (2006)

CFD analysis of CD nozzle and effect of nozzle pressure ratio on pressure and velocity for suddenly expanded flows
by: Khan, Sher Afghan, et al.
Published: (2018)

Active control of base pressure in suddenly expanded flow for area ratio 4.84
by: Ali Baig, Maughal Ahmed, et al.
Published: (2012)

Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes
by: Baig, Maugal Ahmed Ali, et al.
Published: (2012)

Experimental study of suddenly expanded flow from correctly expanded nozzles
by: Khan, Sher Afghan, et al.
Published: (2016)

Enlarge duct length optimization for suddenly expanded flows
by: Pathan, Khizer Ahmed, et al.
Published: (2020)

Base and wall pressure control using cavities and ribs in suddenly expanded flows -an overview
by: Sethuraman, Vigneshvaran, et al.
Published: (2020)

Effect of nozzle pressure ratio and control jets location to control base pressure in suddenly expanded flows
by: Pathan, Khizer Ahmed, et al.
Published: (2019)

Investigation of base flow for an axisymmetric suddenly expanded nozzle with micro JET
by: Chaudhary, Zakir Ilahi, et al.
Published: (2018)

An investigation of effect of control jets location and blowing pressure ratio to control base pressure in suddenly expanded flows
by: Pathan, Khizar Ahmed, et al.
Published: (2020)

Effect of level of expansion and inertia level in a suddenly expanded flow
by: Chaudhary, Zakir Ilahi, et al.
Published: (2015)

Analysis of parameters affecting thrust and base pressure in suddenly expanded flow from nozzle
by: Pathan, Khizar Ahmed, et al.
Published: (2019)

Control of nozzle flow using microjets at supersonic Mach Regime
by: G M, Fharukh, et al.
Published: (2019)

Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow
by: Bashir, Musavir, et al.
Published: (2015)

A cost-effective data acquisition instrumentation for measurement of base pressure and wall pressure in suddenly expanded flow through ducts
by: Sethuraman, Vigneshvaran, et al.
Published: (2019)

Study of effect of flow parameters on base pressure in a suddenly expanded duct at supersonic mach number regimes using CFD and design of experiments
by: Quadros, Jaimon Dennis, et al.
Published: (2018)

Control of base pressure with micro jets:part-I
by: Rehman, Shafiqur, et al.
Published: (2008)

Base pressure behaviour in a suddenly expanded duct at supersonic mach number regimes using Taguchi design of experiments
by: Quadros, Jaimon Dennis, et al.
Published: (2018)

Active control of suddenly expanded flows from overexpanded nozzles
by: Khan, Sher, et al.
Published: (2002)

Role of active control in increasing base pressure at Sonic Mach Number
by: G. M, Fharukh Ahmed, et al.
Published: (2019)

Influence of low length-to-diameter ratio and nozzle pressure ratio in an abruptly expanded flow
by: Khan, Sher Afghan
Published: (2015)

Effect of sudden expansion for varied area ratios at subsonic and sonic flow regimes
by: Sethuraman, Vigneshvaran, et al.
Published: (2016)

Control of nozzle flow in a suddenly expanded duct with micro jets
by: Baig, Maugal Ahmed Ali, et al.
Published: (2012)

Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges
by: Crasta, Asha, et al.
Published: (2012)

Stabilty derivatives in the newtonian limit
by: Crasta, Asha, et al.
Published: (2013)

Stability derivatives of a delta wing with straight leading edge in the Newtonian limit
by: Crasta, Asha, et al.
Published: (2013)

Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD
by: Quadros, Jaimon Dennis, et al.
Published: (2016)

Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for mach 3.0 using CFD.
by: Quadros, Jaimon Dennis, et al.
Published: (2016)

Effect on base pressure in suddenly expanded flows with variable location of microjets
by: Baig, Maugal Ahmed Ali, et al.
Published: (2012)

An investigation to control base pressure in suddenly expanded flows
by: Pathan, Khizer Ahmed, et al.
Published: (2018)

Combined effect of relief and level of expansion in a suddenly expanded flow
by: Syed, Syed Ashfaq, et al.
Published: (2015)

Wall pressure studies in a suddenly expanded flow for area ratio 2.56”
by: Baig, Maugal Ahmed Ali, et al.
Published: (2012)

Effect of mach number in a suddenly expanded flow for area ratio 4.84
by: Baig, Maugal Ahmed Ali, et al.
Published: (2012)

Studies on suddenly expanded flow at different levels of over expansion for area ratio 3.24
by: Baig, Maugal Ahmed Ali, et al.
Published: (2012)

CFD analysis of effect of area ratio on suddenly expanded flows
by: Pathan, Khizer Ahmed, et al.
Published: (2017)

Experimental research on flow development and control effectiveness in the duct at high speed
by: Khan, Sher Afghan, et al.
Published: (2019)

Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56
by: Khan, Sher Afghan, et al.
Published: (2019)

Active control of wall pressure flow field at low supersonic Mach numbers
by: Asad Ullah, Mohammed, et al.
Published: (2016)

Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56
by: Bashir, Musavir, et al.
Published: (2016)

Studies on flow from converging nozzle and the effect of nozzle pressure ratio for area ratio of 6.25
by: Ashfaq, Syed, et al.
Published: (2014)