Computational aeroacoustics and numerical simulation of supersonic jets

final report on NASA grant NAG 1-1479

Publisher: National Aeronautics and Space Administration, Publisher: National Technical Information Service, distributor in [Washington, DC, Springfield, Va

Written in English
Published: Downloads: 625
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  • Aeroacoustics,
  • Supersonic jet flow,
  • Computerized simulation,
  • Boundary conditions,
  • Computational fluid dynamics,
  • Acoustic scattering,
  • Jet aircraft noise

Edition Notes

StatementPhilip J. Morris and Lyle N. Long.
Series[NASA contractor report] -- NASA CR-202239.
ContributionsLong, Lyle N., United States. National Aeronautics and Space Administration.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL17455299M

Paperback. Condition: New. Language: English. Brand new Book. Progress associated with research in (1) physics and prediction of turbulent mixing noise from supersonic jets, and (2) numerical simulation of supersonic jet noise is reported. Tam, Christopher Langley Research Center NASA-CR, NAS NAG In the present work, computational aeroacoustics and parallel computers are used to conduct a study of flow-induced noise from different jet nozzle geometries. The nozzle is included as part of the computational domain. This is important to predict jet noise from nozzles associated with military aircraft engines. The Detached Eddy Simulation (DES) approach is used to simulate both the jet.   Numerical methods including low order correlations and Reynolds-averaged Navier–Stokes (RANS) are known to be deficient for complex configurations and even simple jet flows. Using high fidelity numerical methods such as large eddy simulation (LES) allows conditions to be carefully controlled and quantified. Various gaps in the surface of the supersonic aircraft have a significant effect on airflows. In order to predict the effects of attack angle, Mach number and width-to-depth ratio of gap on the local aerodynamic heating environment of supersonic flow, two-dimensional compressible Navier-Stokes equations are solved by the finite volume method, where convective flux of space term adopts the Roe.

Performance Efficient Jet Noise Reduction for Supersonic Nozzles Google Scholar N. E. Murray & B. J. Jansen. International Journal of Aeroacoustics, 11 (7&8),   The objective of Computational Aeroacoustics [CAA] is not simply to develop computational methods and to use these methods to solve aeroacoustics problems and perform numerical simulation of aeroacoustic phenomena. This is both a textbook with exercises for graduate students and a reference with code for researchers in s: 4. NUMERICAL SIMULATION FOR PROBLEMS OF AERODYNAMICS ON MULTIPROCESSOR COMPUTING SYSTEMS Lutskiy A.E*, Men’shov I.S*, Zabrodin A.V.* *Keldysh Institute of Applied Mathematics RAS, , Miusskaya sq. 4, Moscow, Russia. Key words: computational aerodynamics, massively parallel systems, supersonic wing-tip vortices, jet flows, screech jet noise.   About this journal. International Journal of Aeroacoustics is a peer-reviewed journal publishing developments in all areas of fundamental and applied aeroacoustics. Fundamental topics include advances in understanding aeroacoustics phenomena; applied topics include all aspects of civil and military aircraft, automobile and high speed train aeroacoustics, and the impact of acoustics on .

Computational simulations have thus been the primary tool for recent jet noise sound generation studies, despite notable limitations for practical aircraft jet noise problems. Most numerical simulation methods involve the solution of some form of the basic equations of . Matthew Kapusta, Russell Powers, Philip J Morris and Dennis McLaughlin, , "Numerical simulations for supersonic jet noise reduction", AIAA, AIAA Paper B. Cheng, Y. Han, Kenneth S Brentner, Jose Palacios, Philip J Morris, D. Hanson and Michael P Kinzel, , "Rotor broadband noise due to surface roughness during ice accretion. In these lecture notes, we discuss the goals of computational aeroacoustics (CAA) and the numerical techniques that have been developed to achieve them. We first survey the scientific and engineering issues that have motivated computational approaches to aeroacoustic prob-lems over the past few decades, and define choices of flow model and. NUMERICAL SIMULATION OF FREE SHEAR FLOWSTowards a Predictive Computational Aeroacoustics Capability W.Y. Soh Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio Summary Implicit and explicit spatial differencing techniques with fourth order accuracy have been developed. The implicit technique is based on the Pade.

Computational aeroacoustics and numerical simulation of supersonic jets Download PDF EPUB FB2

Get this from a library. Computational aeroacoustics and numerical simulation of supersonic jets: final report on NASA grant NAG [Philip J Morris; Lyle N Long; United States. National Aeronautics and Space Administration.]. In this study, the noise generated from a cold supersonic circular twin jet is simulated with a high-order finite difference solver.

The three-dimensional compressible Favre-filtered Navier–Stokes equations in Cartesian form are solved by computational aeroacoustics by: 2.

Numerical simulations of supersonic jet flows. Shih-Chieh Lo, Purdue University. Abstract. Supersonic jet flows are studied using 3-D large eddy simulation (LES).

The farfield noise generated by the jets is investigated by a computational aeroacoustics (CAA) methodology that couples the near field unsteady flow field data computed by 3-D LES with a surface integral acoustic method for noise Cited by: 3. Numerical Simulation of Supersonic Jet Flows and their Noise S.-C.

Lo⁄, G. Blaisdell y, and A. Lyrintzis z School of Aeronautics and Astronautics Purdue University West Lafayette, IN Large-eddy simulations (LES) of a circular supersonic fully expanded jet and an under-expanded jet Cited by: The focus of this research project lies in the numerical simulation of jet screech.

Different numerical methods are shown with LES and DNS applications of a planar rectangular and three-dimensional jet with overset grid techniques to include complex geometries for the jet by: 8.

Numerical Simulation of Supersonic Combustion for Hypersonic Propulsion model shows good prediction for mixing layer and jet flow problems, and that it is also less sensitive to initial values [12].

is a magnified plot of the computational grid around the. the case of direct numerical simulation of supersonic jet flows and noise radiation will be used.

The second objective is to review re-cently developed computational methods designed especially for CAA applications.

Before one designs a computational algorithm for simulating supersonic jet noise generation and radiation, it is important that.

Computational aeroacoustics beneath high speed transitional and turbulent boundary layers. Direct numerical simulation. Structural elements of supersonic and hypersonic aircraft are exposed to acoustic fatigue due to pressure fluctuations beneath the transitional or turbulent boundary layers (TBLs), as well as to shock-wave boundary.

1. Powell, “ On the noise emanating from a two-dimensional jet above the critical pressure,” Aeronaut.Q. 4, ().Google Scholar Crossref; 2. Shen and C. Tam, “ Numerical simulation of the generation of axisymmetric mode jet screech tones,” AIAA J.

36, (). Google Scholar Crossref; 3. Thies and C. Tam, “ Computational of turbulent. A numerical representation of a PDE gives rise to an approximate solution. A consistent, stable, and convergent high order scheme does not guarantee good numerical wave solutions. Vortical and entropic waves are nondispersive, nondissipative, and directional Acoustic waves are nondispersive, nondissipative, and propagate with s.o.s.

Freund, J.B.: Acoustic sources in a turbulent jet: a direct numerical simulation study. 5th AEAA/CEAS Aeroacoustics Conference, AIAA PaperBellevue, WA, 10–12 May Google Scholar Freund, J.B.: Noise source at in low reynoldsnumber turbulent jet.

Fluid Mech. – () zbMATH CrossRef Google Scholar. Mach numbers ranging from tosupersonic jets containing weak shocks and Mach disks, and supersonic jets with nonaxisymmetric nozzle exit geometries.

This report discusses computational methods, code implementation, computed results, and comparisons with available experimental data.

Very good agreement is shown. Instability waves have been established as the dominant source of mixing noise radiating into the downstream arc of a supersonic jet when the waves have phase velocities that are supersonic relative to ambient conditions.

Recent theories for supersonic jet noise have used the concepts of growing and decaying linear instability waves for predicting radiated noise. A review of aeroacoustics of supersonic jets interacting with solid surfaces. Validation of a Computational Aeroacoustics Code for Nonlinear Flow about Complex Geometries Using Ringleb's Flow.

Direct numerical simulation of 3-D jets. Liu, K. Kailasanath, N. Heeb, D. Munday and E. Gutmark, Large-eddy simulations of a supersonic heated jet, in 17th AIAA/CEAS Aeroacoustics Conf. (32nd AIAA Aeroacoustics Conference) (American Institute of Aeronautics and Astronautics, ), pp.

Questions, ranging from the role numerical methods play in the classical theoretical approaches to aeroacoustics, to the correct specification of well-posed numerical problems, need to be answered.

These issues provided the impetus for the Workshop on Computa­ tional Aeroacoustics sponsored by ICASE and the Acoustics Division of NASA LaRC on.

Computational aeroacoustics calculations, based on direct numerical simulations, were performed in order to predict the near‐field and far‐field sound radiated by a forced, round, unconfined, subsonic jet.

The jet Mach number was around Ma=, and the Reynolds number based on the jet velocity and diameter was approximately Re= The compressible Navier–Stokes equations were integrated.

Supersonic impinging jets can be found in different technical applications of aerospace engineering. Depending on the flow conditions, loud tonal noise can be emitted. The so-called impinging tone is investigated by researchers of the chair of computational fluid dynamics at the Technical University of Berlin.

Using direct numerical simulations (DNS) carried out on the Cray HPC systems Hermit. 1) is a supersonic jet exhausted from nozzle 2. A jet from the third nozzle (nozzle 3) is an assisting jet for the supersonic jet from nozzle 2. A detailed role of nozzle 3 is assessed and described in Section Outlet conditions and a schematic illustration of the coaxial triple supersonic jets are given in Table 1 and Fig.

1 Simulation model. Computational approaches are being developed to study a range of problems in aeroacoustics. These aeroacoustic problems may be classified based on the physical processes responsible for the sound radiation, and range from linear problems of radiation, refraction, and scattering in known base flows or by solid bodies, to sound generation by turbulence.

Computational aeroacoustics is a branch of aeroacoustics that aims to analyze the generation of noise by turbulent flows through numerical methods. Such numerical methods can be far field integration methods is that the sound source is not compact in supersonic flow. Errors could be encountered in calculating the sound field, unless the.

Computational Aeroacoustics—A Wave Number Approach Christopher K. Cambridge University Press,pp. Price: $ (hardcover). ISBN: ISBN: Chris Tam has given in this book a valuable and very pleasing account of how to resolve the peculiar difficulties encountered in the numerical.

Computational Aeroacoustics. Edited by Ganesh Raman Publication date: December • ISBN • vii + pp • £ about the book. Computational Aeroacoustics (CAA) deals with the simulation of sound generated by unsteady flows and is a rapidly growing area due to advances in computational power and the significant.

Advances in computational aeroacoustics (CAA) Numerical Simulation of Three-Dimensional Supersonic Jet Screech Tones. Xiaodong Li and Junhui Gao. 11 November Three-dimensional numerical simulation of the jet screech phenomenon.

Hao Shen and C. Tam. 22 August Numerical simulation of mixing enhancement in a hot supersonic jet Physics of Fluids 9 “Supersonic jet noise and the high speed civil transport,” AIAA Paper 89–, D. Hanson-Parr, and U. Obeysekare, “ Streamwise and spanwise vortex interaction in an axisymmetric jet.

A computational and experimental study,” Phys. Computational AeroAcoustics, or CAA, covers the development of innovative numerical methods for the simulation of the propagation of acoustic waves in three-dimensional regions characterized by.

Computational Aeroacoustics is a field that deals with the simulation of sound generated by unsteady flows and is a rapidly growing area due to advances in computational power and the significant projected growth in global transportation.

With the era of widespread supersonic flight and the prolifer. of computers, the application of Direct Numerical Sim-ulation(DNS) and Large Eddy Simulation(LES) to jet noise prediction methodologies is becoming more fea-sible.

The first DNS of a turbulent jet was done for a Reynolds number 2, supersonic jet at Mach. Predicting jet noise is currently a challenge even for subsonic jet engines. State-of-the-art Computational Fluid Dynamics (CFD) methods, such as Large-Eddy Simulation, can accurately capture the noise sources in the jet near-field, but using the same methods to compute the noise propagation to the far-field is still prohibitively expensive.

Supersonic Jet Flow The picture shows a snap shot of the flow field generated when fluid leaves a convergent-divergent nozzle at supersonic conditions. The interaction of turbulence structures and shocks in the supersonic jet can be simulated using Computational Fluid Dynamics (CFD) based on the compressible form of the Navier-Stokes equations.

Shen, H. Tam, C.K.W. Numerical Simulation of the Generation of Axisymmetric Mode Jet Screech Tones AIAA Journal 36 Sherer, S. E. Spalart, P.R. Allmaras, S.R. A one-equation turbulence model for aerodynamic flows La Recherche Aerospatiale 1 5.A lot of the emitted noise is created in the jet wake behind aircraft engines.

This project aims at the prediction of aeroacoustic jet noise. To this end, we develop and use various numerical methods for computational aeroacoustics, such as DNS, LES and acoustic far-field solvers.Computational Aeroacoustics. Computational aeroacoustics involves the numerical simulation of the unsteady flow and the noise it produces.

Predictions can be based on steady or unsteady flow calculations. In the former case, knowledge of the average flow allows the radiated noise to be estimated using analytical methods.