Supersonic mixing enhancement by vorticity for high-speed propulsion

final report for the period April 1, 1988 - June 30, 1991
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PennState Gas Dynamics Laboratory, National Aeronautics and Space Administration, National Technical Information Service, distributor , [College Park, Penn.], [Washington, DC, Springfield, Va
Vortex-mo
Statementsubmitted by Gary S. Settles.
SeriesNASA contractor report -- NASA CR-188920.
ContributionsUnited States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15369986M

This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. Supersonic mixing enhancement by vorticity for high-speed propulsion Supersonic mixing enhancement by vorticity for high-speed propulsion by Settles, Gary S.

Publication date Language English. The results of a three year study on vortex enhancement of supersonic mixing are discussed. Recent interests in compressible mixing.

Get this from a library. Supersonic mixing enhancement by vorticity for high-speed propulsion: final report for the period April 1, - J [G S Settles; United.

Description Supersonic mixing enhancement by vorticity for high-speed propulsion FB2

Triangular tabs for supersonic jet mixing enhancement - Volume Issue - Arun Kumar P., E. RathakrishnanCited by: 2. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Based on the fact that complicated flow phenomena exist in the supersonic combustor, i.e., shock waves and turbulence, Drummond et al.

[19, 20, 23] studied the enhancement of shock waves on mixing. An analysis for predicting the interaction of a steady oblique shock wave and a planar mixing region is presented.

Specifically, an equation for the shock curvature was obtained from the shock wave and isentropic wave difference equations which govern the shock transmission within a region of varying Mach by: Request PDF | Mixing Enhancement Induced by a Delta Wing in Supersonic Flows | The maximization of rapid fuel-air mixing is one of the essential issues for the efficient operation of scramjet engines.

“Mixing and mixing enhancement in supersonic reacting flow fields,” in Murthy, S. and Curran, E. T., editors, High Speed Propulsion Systems,volume of AIAA Progress Series,chapter 7, pages –, American Institute of Aeronautics and by:   The view from inside supersonic combustion Designing scramjets with extremely high-speed propulsion just got easier: Numerical simulations.

ADVANCED PROPULSION SYSTEM STUDIES IN HIGH SPEED RESEARCH Charles L. Zola* University of Toledo Toledo, Ohio SUMMARY Propulsion for acceptable supersonic passenger transport aircraft is primarily impacted by the very high jet noise characteristics of otherwise attractive engines.

The mixed flow turbofan, when equipped with a special ejector. A summary of the propulsion system modeling under NASA’s High Speed Project (HSP) AeroPropulsoServoElasticity (APSE) task is provided with a focus on the propulsion system for the low- boom supersonic configuration developed by Lockheed Martin and referred to as the N+2 configuration.

An experimental and computational investigation of a combination of fluidic injection and chevrons (fluidically enhanced chevrons) for supersonic jet noise reduction was performed.

Previous studies have shown that chevrons underperform in overexpanded flow due to reductions in effective penetration. Consequently, this study focuses on improvements gained by fluidic enhancement in the Cited by: In air breathing propulsion systems for flight at Mach numbers 7 to 20, it is generally accepted that the combustion processes will be carried out at supersonic velocities with respect to the engine.

The resulting brief residence time places a premium on rapid mixing of the fuel and by: Supersonic Retro-Propulsion Experimental Design for Computational Fluid Dynamics Model Validation Scott A. Berry (@, ) Supplemental data included high-speed Schlieren video and internal pressures and temperatures.

File Size: 7MB. Numerical Analysis Of Turbulence Mixing By Shockwave Interaction In Scramjet Combustor Scram jets are designed to operate in the hypersonic flight regime, beyond the reach of turbojet engines, and along with ramjets, fill the gap between the high efficiency of turbojets and high speed of rocket engines.

Srikrishnan A. completed his Ph. from IIT Madras inin the field of fuel-air mixing and combustion in supersonic flows as applied to advanced aerospace propulsion systems.

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Industrial Experience: Worked for 16 years with the global leaders in CAE Fluent Inc and ANSYS holding leadrship positions. (2) non-air-breathing jet propulsion systems or rocket propulsion systems. The subject matter of this book is rocket propulsion systems.

However, for the sake of completeness and continuity, let us consider briefly the classification of air-breathing propulsion systems. Fig. File Size: 1MB. Jet Propulsion Engines: High Speed Aerodynamics and Jet Propulsion, V12 [Otis E.

Lancaster, Coleman Dup Donaldson, Theodore Von Karman] on *FREE* shipping. Both the Air Force Research Lab (AFRL) and the Air Force Institute of Technology (AFIT) at Wright-Patterson Air Force Base in Ohio are investigating the enhancement of fuel-air mixing with small pylons that project into the supersonic flow upstream of a flame holder cavity.

High-Speed Flows & Propulsion AA Compressible Fluid Mechanics Reviews the fundamentals with application to external and internal flows; supersonic flow, 1D and Quasi-1D, steady and unsteady flow, oblique shocks and expansion waves, linearized flow, 2D flow, method of characteristics; and transonic and hypersonic flow.

To promote efficient performance of very high speed air-breathing propulsion systems, the combustor Mach number must be of the order of six for a flight Mach number of Because of this high gas speed through the combustor, mixing rates of hydrogen fuel with air must be very rapid in order to allow a combustor of reasonable length.

High Speed Aerodynamics and Jet Propulsion, Volume 7: Aerodynamic Components of Aircraft at High Speeds [Donovan, A.F., and H.R. Lawrence, editors] on *FREE* shipping on qualifying offers. High Speed Aerodynamics and Jet Propulsion, Volume 7: 5/5(1). Studies on supersonic free jets from complex nozzles are few, like the study on radially lobed nozzle using the schlieren technique by Srikrishna et ative studies have focused on aero-acoustic noise reduction like Tide and prompted the authors to conduct a detailed study on the near field of the jet using the PLIF (Planar Laser Induced Florescence) technique, pitot Cited by: 1.

Experimental and Computational Studies on Supersonic Helium Mixing with Swept Ramp Injector. Aso, S. / Yamane, Fuel/Air Mixing Enhancement by Cantilevered Ramp Injectors in Hypersonic Flows. Sislian, Material Challenges and Progress Toward Meeting the High-Speed Civil Transport Propulsion Design Requirements.

Johnson, A. / Bartlett. New Trends in Fluid Mechanics Research is the proceedings of the Fifth International Conference on Fluid Mechanics (ICFM-V); it is the primary forum for the presentation of technological advances and research results in the fields of theoretical, experimental, and computational Fluid Mechanics.

Influence of vorticity distribution on singularities in linearized supersonic flow Physics of Flu ( work that the presence of the singularity at the cone of influence is associated with the step-function nature of the vorticity distribution specified in the canonical case.

“ Turbulent mixing,” Annu. Rev. Fluid Author: Vijay Gopal, Luca Maddalena. High-Speed Aerodynamics – Subsonic, Transonic, and Supersonic Flight. in Physics. When an airplane is flying at subsonic speed, all of the air flowing around the airplane is at a velocity of less than the speed of sound (known as Mach 1).

Keep in mind that the air accelerates when it flows over certain parts of the airplane, like the top of.

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Podded Propulsor / Z-Drive. Propulsion of a ship has traditionally been accomplished by using one or several rotating propellers and steering has been accomplished by making use of one or more.

interaction Vorticity LIA DNS Lamb vector 1 Introduction The interaction of shock waves with turbulence is an impor-tant aspect in many types of flows, from hypersonic flight, to supersonic combustion, to astrophysics and Inertial Con-finement Fusion (ICF).

In general, the shock width is muchCited by:. Herein, a supersonic combustion coherent jet is proposed based on current coherent jet technology to improve the impact capacity of a coherent jet and increase the stirring intensity of the electric arc furnace (EAF) bath.

Further, numerical simulations and an experimental analysis are combined to study the supersonic combustion coherent jet characteristics, including the Mach number, dynamic Author: Fei Zhao, Rong Zhu, Wenrui Wang.Propulsion1 is developing and using three different types or generations of computational models for high speed flows.

Generation I models are based on Reynolds-averaged Navier-Stokes (RANS) closures and are currently being used by center researchers for the development and testing of new concepts and design of high speed propulsion by: 8.Three compressible mixing layers, with one supersonic and one subsonic streams, for convective Mach numbers ofand are experimentally studied by laser anemometry.

Detailed measurements of the mean and fluctuating velocity fields are Cited by: 8.