Book Description
Keywords: adaptive mesh, dynamic solution-adaptive, unsteady transformation.
Author : Michael Dean Neaves
Publisher :
Page : 64 pages
File Size : 11,31 MB
Release : 2001
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Keywords: adaptive mesh, dynamic solution-adaptive, unsteady transformation.
Author :
Publisher :
Page : pages
File Size : 33,38 MB
Release : 2001
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The numerical investigation into the dynamics of unsteady inlet flowfields is applied to a three-dimensional scramjet inlet-isolator-diffuser geometry designed for hypersonic type applications. The Reynolds-Averaged Navier-Stokes equations are integrated in time using a subiterating, time-accurate implicit algorithm. Inviscid fluxes are calculated using the Low Diffusion Flux Splitting Scheme of Edwards. A modified version of the dynamic solution-adaptive point movement algorithm of Benson and McRae is used in a coupled mode to dynamically resolve the features of the flow by enhancing the spatial accuracy of the simulations. The unsteady mesh terms are incorporated into the flow solver via the inviscid fluxes. The dynamic solution-adaptive grid algorithm of Benson and McRae is modified to improve orthogonality at the boundaries to ensure accurate application of boundary conditions and properly resolve turbulent boundary layers. Shock tube simulations are performed to ascertain the effectiveness of the algorithm for unsteady flow situations on fixed and moving grids. Unstarts due to a combustor and freestream angle of attack perturbations are simulated in a three-dimensional inlet-isolator-diffuser configuration.
Author : D. McRae
Publisher :
Page : 38 pages
File Size : 31,29 MB
Release : 1998
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Completed research is reported for an dynamic numerical investigation of unsteady flow in supersonic and hypersonic aircraft inlets. An explicit dynamic solution adaptive mesh computational code was further developed and used to obtain dynamic solutions for an axisymmetric mixed compression inlet and a generic dual mode scramjet inlet isolator diffuser combination. To improve robustness, an existing implicit code was modified for time accuracy and the solution adaptive mesh algorithm was installed. The inlet unstart phenomenon was simulated through perturbation of freestream and downstream conditions (axisymmetric inlet) and through downstream throttling for the dual mode 3-D configuration. Axisymmetric unstart could be induced by a 10% freestream temperature increase or a 5% backpressure increase. Comparison of the results with experiment, where available, indicate that stability margins assessed through inviscid design or quasi-steady experiment may need revision when dynamics are considered. Conclusions are drawn concerning specifics of the flow phenomena and directions for future research are suggested. Lack of highly resolved dynamic experimental data is a pacing item and will prevent full verification of future work.
Author :
Publisher :
Page : 47 pages
File Size : 40,41 MB
Release : 1994
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Research has been performed to obtain very accurate dynamic simulations of supersonic inlet unstart using CFD codes and a dynamic solution adaptive mesh algorithm developed at NCSU. The codes use Runge-Kutta time differencing and Advective Upwind Split Method spatial differencing in finite volume form. Other changes have been incorporated to improve the time accuracy when the computational mesh is dynamically adapted. Solutions have been obtained and animated for unstart of generic 2-D mixed compressions and fully supersonic inlets. Analysis of results revealed that laminar viscous flow unstart occurs by a separation/oblique shock mechanism rather than movement of a normal shock. Turbulent flow simulations reveal that initial shock motion occurs initially but then reverts to the separation/oblique shock mechanisms. 3-D steady and unsteady simulations are presented and conclusions drawn concerning the role of separation in inlet unstart. Computational fluid dynamics, Dynamic adaptive mesh, Mixed compression inlet unstart, Unsteady flow.
Author :
Publisher :
Page : 854 pages
File Size : 21,99 MB
Release : 2002
Category : Dissertations, Academic
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Author :
Publisher :
Page : 464 pages
File Size : 38,67 MB
Release : 1995
Category : Aeronautics
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Author : Keith E. Numbers
Publisher :
Page : 60 pages
File Size : 23,62 MB
Release : 1994
Category : Aerodynamics, Supersonic
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A comprehensive review of techniques and methods for applying computational fluid dynamics (CFD) analysis to high speed inlets and related flows is provided via an extensive literature survey of such applications. Topics covered include governing equations, numerical integration schemes, boundary conditions, gridding requirements, and turbulence models. Results of applications from the literature survey shed light on the relative success of the techniques being used throughout the industry. (AN).
Author :
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Page : 538 pages
File Size : 44,75 MB
Release : 1991
Category : Aeronautics
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Author : Michael D. Neaves
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Page : pages
File Size : 34,93 MB
Release : 2001
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Author :
Publisher :
Page : 1484 pages
File Size : 34,60 MB
Release : 1995
Category : Government publications
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