Passive control of pressure oscillations in hypersonic cavity flow PDF Download
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Author: Shiaw-wuu Perng
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 260
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Book Description
Author: Shiaw-wuu Perng
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 260
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Book Description
Author: D. S. Dolling
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 140
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Book Description
An experimental study of open cavity flow has been made in a high Reynolds number, Mach 5 turbulent boundary layer. The majority of measurements made were of fluctuating wall pressures. The objectives were: (1) examine how effective changes in front and rear wall geometry were at attenuating the pressure oscillations, (2) explore how impingement of a shock wave (variable strength and position) the cavity flow, and (3) how stores (different geometries and positions) affected the cavity flow. In addition, techniques which were judged effective at attenuating pressure oscillations for the empty cavity were used with shock impingement and with stores in order to explore their effectiveness under perturbed flow conditions. The results show that vented and slotted walls, and spoilers are ineffective. A 3-D rear wall (swept in both planes and symmetric about the center line) attenuated the strongest oscillations by factors of up to 7 compared to the baseline rectangular cavity. Regardless of shock impingement position, shock strength, store position, store dimensions, store to cavity volume ratio and asymmetric store arrangement the cavity oscillation frequencies remain essentially unchanged. Based on the mean and rms Pressure distributions (whose magnitude varies substantially but whose basic shape does not change significantly) and surface flow patterns it appears that the essential flow structure also remains largely unchanged. These similarities suggest that control techniques developed for the empty cavity flow should be effective with shock impingement or store release. Tests using two passive control rear walls in perturbed cavity flow support this conclusion.
Author: Mostafa Barzegar Gerdroodbary
Publisher: Butterworth-Heinemann
ISBN: 0128211407
Category : Technology & Engineering
Languages : en
Pages : 230
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Book Description
Scramjet engines are a type of jet engine and rely on the combustion of fuel and an oxidizer to produce thrust. While scramjets are conceptually simple, actual implementation is limited by extreme technical challenges. Hypersonic flight within the atmosphere generates immense drag, and temperatures found on the aircraft and within the engine can be much greater than that of the surrounding air. Maintaining combustion in the supersonic flow presents additional challenges, as the fuel must be injected, mixed, ignited, and burned within milliseconds. Fuel mixing, along with the configuration and positioning of the injectors and the boundary conditions, play a key role in combustion efficiency. Scramjets: Fuel Mixing and Injection Systems discusses how fuel mixing efficiency and the advantage of injection systems can enhance the performance of the scramjets. The book begins with the introduction of the supersonic combustion chamber and explains the main parameters on the mixing rate. The configuration of scramjets is then introduced with special emphasis on the main effective parameters on the mixing of fuel inside the scramjets. In addition, basic concepts and principles on the mixing rate and fuel distribution within scramjets are presented. Main effective parameters such as range of fuel concentration for the efficient combustion, pressure of fuel jet and various arrangement of jet injections are also explained. This book is for aeronautical and mechanical engineers as well as those working in supersonic combustion who need to know the effects of compressibility on combustion, of shocks on mixing and on chemical reactions, and vorticity on the flame anchoring. - Explains the main applicable approaches for enhancement of supersonic combustion engines and the new techniques of fuel injection - Shows how the interaction of main air stream with fuel injections can develop the mixing inside the scramjets - Presents results of numerical simulations and how they can be used for the development of the combustion engines
Author:
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 686
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Book Description
Author: American Institute of Aeronautics and Astronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 868
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Book Description
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 636
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 714
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Book Description
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 500
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1016
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Book Description
Author: Kenneth M. Nicoll
Publisher:
ISBN:
Category :
Languages : en
Pages : 80
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Book Description
The present report describes an experimental investigation of a hypersonic cavity flow with mass-injection into the separated-flow region. The experiments were carried out in a helium wind-tunnel at a free-stream Mach number of eleven. The injected gas was helium. Two parameters were varied during the study -- the mass injection rate and the height of the separation shoulder relative to the reattachment shoulder. The effects of these parameters on the distributions of pressure and heat transfer rate were investigated. Mass injection appeared to have no drastic effect on transition Reynolds number, and the cavity flow is believed to have been laminar throughout the present investigation. The effect on the cavity floor pressure of raising the separation shoulder relative to the reattachment shoulder was of the same order as the effect of mass injection, the two effects being virtually independent of one another. However, the flow in the immediate vicinity of the reattachment shoulder and downstream was primarily controlled by mass injection rate. Small amounts of mass injection were capable of completely removing the pressure peak at reattachment, and could produce a flow with almost constant pressure within and downstream of the cavity. Mass injection had a pronounced effect on the heat transfer rate in the vicinity of reattachment, and reductions of as much as a factor of six were obtained in the heat transfer peak in this region. Furthermore, the heat transfer rates up to about one cavity length downstream of the reattachment shoulder were reduced by as much as a factor of three by mass injection within the cavity. (Author).
