Transonic Navier-Stokes solutions of three-dimensional afterbody flows



Publisher: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, Publisher: For sale by the National Technical Information Service] in [Washington, DC], [Springfield, Va

Written in English
Published: Downloads: 742
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Subjects:

  • Aerodynamics, Transonic.,
  • Navier-Stokes equations.

Edition Notes

StatementWilliam B. Compton III ... [et al.].
SeriesNASA technical memorandum -- 4111.
ContributionsCompton, William B., United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15289802M

Hybrid methods can be used for efficiency, typically using Navier-Stokes solutions near the blade and some vortex method for the rest of the flow field. Sources for the derivations of the equations are Lamb (), Morse and Feshback (), Garrick (), A shley and Landahl (), and Batchelor (). Computed solutions of the time-dependent, Reynolds-averaged Navier-Stokes equations for three dimensional flows having thin shear layers are analyzed using. The forebody flowfield can then be used as a boundary condition and the thin-shear-layer Navier-Stokes solution advanced in time to a steady state in the afterbody region only. This is the procedure adopted in the present stiidy. The parabolized Navier-Stokes solutions are obtained using the conical flow and marching codes of Schiff and Steger. The three-dimensional ideal gas flow in the shock layer of a blunted supersonic cone at an angle of attack is calculated using two asymptotic solutions. The first solution calculates the steady state flow in the subsonic nose region by obtaining a time-dependent solution of the hyperbolic equations using numerical techniques.

Transonic Navier-Stokes solutions of three-dimensional afterbody flows / (Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ; Springfield, Va. Solutions of the Euler Equations for Flows over Configurations at High Angles of Attack. Pages Rom, Josef. Preview Buy Chap95 € Solutions of the Navier-Stokes Equations for Flows over Configurations at High Angles of Attack. Pages Rom, Josef Book Subtitle Subsonic, Transonic, and Supersonic Flows Authors. Josef. A zonal, implicit, time-marching Navier-Stokes computational technique has been used to compute three dimensional transonic flow fields over a projectile. Flow field computations have been performed at M for spin rates of 0 and rpm and at angles of attack, alpha 0,4, and 10 degrees. All the computations have been performed on the Cray-2 supercomputer. Also addressed are: three-dimensional flow analysis of turboprop inlet and nacelle configurations, application of computational methods to the design of large turbofan engine nacelles, comparison of full potential and Euler solution algorithms for aero-propulsive flow field computations, subsonic/transonic, supersonic nozzle flows and nozzle Author: S. N. B. Murthy.

It solves the unsteady set of three-dimensional Navier-Stokes equations, completed by a mixing-length turbulence model, using a finite volume technique. The multi-domain approach of the code has facilitated the treatment of this type of geometry. The injection holes are discretized on cylindrical subdomains which overlap the mesh of the main flow. COMPUTATIONS of transonic flows over a practical wing shape are carried out using three-dimensional Reynolds-averaged “thin-layer” Navier-Stokes equations. Computations are done for several angles of attack and the results reveal the flow pattern for each case.   Throughflow calculations are still an inevitable step in the aerodynamic design of compressors. The viscous throughflow model derived from Navier-Stokes equations can be more capable in predicting choked flow and capturing shock waves compared to the traditional methods. In this paper, authors further developed the inviscid model for a previously developed throughflow analysis . A rephrased form of Navier-Stokes equations is performed for incompressible, three-dimensional, unsteady flows according to Eulerian formalism for the fluid motion. In particular, we propose a geometrical method for the elimination of the nonlinear terms of these fundamental equations, which are expressed in true vector form, and finally arrive.

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Transonic Navier-Stokes Solutions of Three-Dimensional Afterbody Flows William B. ComptonJames L. Thomas, William K. Abeyounis, and Mary L.

Mason LangZey Research Center Hampton, Virginia National Aeronautics and Space Administration Office of Management Scientific and Technical Information Division I. Transonic Navier-Stokes solutions of three-dimensional afterbody flows (SuDoc NAS ) [NASA] on *FREE* shipping on qualifying offers.

Transonic Navier-Stokes solutions of three-dimensional afterbody flows (SuDoc NAS ). Free 2-day shipping. Buy Transonic Navier-Stokes Solutions of Three-Dimensional Afterbody Flows at Get this from a library. Transonic Navier-Stokes solutions of three-dimensional afterbody flows. [William B Compton; United States.

National Aeronautics and Space Administration. Scientific and Technical Information Division.;]. - Buy Transonic Navier-Stokes Solutions of Three-Dimensional Afterbody Flows book online at best prices in India on Read Transonic Navier-Stokes Solutions of Three-Dimensional Afterbody Flows book reviews & author details and more at Author: National Aeronautics and Space Adm Nasa.

Three-dimensional subsonic and transonic viscous/inviscid interacting flows were Solution of three-dimensional afterbody flow using reduced Navier-Stokes Lilienthalplatz 7, D Braunschweig.

Introduction A three-stage Runge-Kutta scheme and an implicit LUSGS scheme as additional option is implemented to advance the solutions in time for. Transonic Navier-Stokes solutions of three-dimensional afterbody flows: NASA, National Aeronautics and Space Administration: Books - or: National Aeronautics and Space Administration NASA.

Transonic Navier-Stokes Solutions of Three-Dimensional Afterbody Flows: Nasa, National Aeronautics and Space Adm: : BooksAuthor: National Aeronautics and Space Adm Nasa.

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Fast and free shipping free returns cash on delivery available on eligible : National Aeronautics and Space Adm Nasa. Buy Transonic Navier-Stokes solutions of three-dimensional afterbody flows (SuDoc NAS ) by NASA (ISBN:) from Amazon's Book Store.

Author: NASA. Navier-Stokes solutions of transonic nozzle flow with shock-induced flow separations. Chih Fang Shieh ; Three dimensional flow computations and thrust predictions in 2DCD overexpanded nozzles. Navier-Stokes simulation of nozzle-afterbody flows with jets at off-design conditions.

Transonic Navier-Stokes solutions of three-dimensional afterbody flows eBook: NASA, National Aeronautics and Space Administration: : Kindle StoreAuthor: National Aeronautics and Space Administration NASA.

Navier-Stokes analysis of cold scramjet-afterbody flows. scheme that calculates the transonic flow field over an airfoil. or equal to those of the Navier-Stokes solutions, and the present. Navier-Stokes solutions of transonic nozzle flow with shock-induced flow separations.

SHIEH; C. SHIEH. An implicit three-dimensional Navier-Stokes solver for compressible flow. 3-D Navier-Stokes simulation of turbulent afterbody/nozzle flows. Three dimensional transonic viscous flow computations are presented for a generic high-speed accelerator model which includes wing, body, filets,and a no-flow through engine nacelle.

solutions are obtained from an algorithm for the compressible Navier-Stokes equations which incorporated an upwind-biased, flux-vector-splitting approach along with longitudinally-patched grids. The flow over afterbody geometries was investigated using the reduced Navier-Stokes (RNS) approximation.

Both pressure velocity flux-split and composites velocity primitive variable formulations were considered. Pressure or pseudopotential relaxation procedures are combined with sparse matrix or coupled strongly implicit algorithms to form a three-dimensional solver for general non-orthogonal.

Jennions, I. K., and Turner, M. "Three-Dimensional Navier-Stokes Computations of Transonic Fan Flow Using an Explicit Flow Solver and an Implicit κ–ϵ Solver." Proceedings of the ASME International Gas Turbine and Aeroengine Congress and Exposition.

Volume 1: Turbomachinery. Cologne, Germany. June 1–4, VT01A ASME. Three-dimensional Navier-Stokes simulations have been made for the transonic flow past a nonaxisymmetric nozzle typical of those advocated for advanced fighter airplanes.

Jet exhaust simulation is evaluated as are the Baldwin-Lomax () and Goldberg () turbulence models. The NPARC code, a Reynolds-averaged full Navier-Stokes code, was validated for nozzle afterbody (boatail) flow fields at transonic speeds. The flow fields about three geometries were studied: an.

Kordulla, W., The Computation of Three-Dimensional Transonic Flows With an Explicit-Implicit Method. Proceedings, 5th GAMM-Conf.

Numerical Methods in Fluid Dynamics. Notes On Numerical Fluid Mechanics, Vol. 7, Vieweg Verlag, Wiesbaden, pp. – Google Scholar. The solution of the resulting Navier-Stokes equations presents a formidable problem, especially when the Reynolds number is high so that the length scales relevant to the parabolic terms and to the convective terms become widely disparate.

shock-free configurations in two- and three-dimensional transonic flow; and steady-state solution of. H. AImahroos, P. Khosla and S. Rubin, "Solution of three-dimensional afterbody flows using reduced Navier-Stokes equations," Presented at Computational Fluid Dynamics Symposium on Aeropropulsion, NASA Lewis Research Center, NASA CPNumerical solutions of the Navier-Stokes equations for transonic afterbody flows (OCoLC) Microfiche version: Swanson, R.

Charles. Numerical solutions of the Navier-Stokes equations for transonic afterbody flows (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document.

Computed solutions of the time-dependent, Reynolds-averaged Navier-Stokes equations for three-dimensional flows having thin shear layers are analyzed, using topological concepts. Specific examples include the transonic flow over a body of revolution with conical afterbody at moderate angles of incidence to the free stream.

starting solution over the afterbody based on the forebody solution. The forebody flowfield can then be used as a boundary condition and the thin-shear-layer Navier-Stokes solution advanced in time to a steady state in the afterbody region only. This is the procedure adopted in the present study.

The parabolized Navier-Stokes solutions are obtained. For transonic flow cases, the Enquist-Osher flux biasing scheme developed for the full potential equation is used.

A quasi-conservation form of the governing equations is used in the shock region to capture the correct rotational behavior. The composite velocity procedure is applied for the solution of three-dimensional afterbody problems. Two- and three-dimensional, steady and unsteady viscous flow fields are numerically simulated by solving the Navier-Stokes equations.

A solution-adaptive-grid method is used to redistribute the grid points so as to improve the resolution of shock waves and shear layers without increasing the number of grid points. Flow fields considered include two-dimensional transonic flows about airfoils.

Buffeting flow on transonic aerofoils serves as a model problem for the more complex three-dimensional flows responsible for aeroplane buffet.

The origins of transonic aerofoil buffet are linked to a global instability, which leads to shock oscillations and dramatic lift fluctuations. Two Dimensional Euler and Navier-Stokes Solutions of Flow Over the Mid Section of a Car, 2nd IAVD Congress on Vehicle Design and Components, Geneva, Google Scholar 3.

Leicher, S. Analysis of Transonic and Supersonic Flows Around Wing-Body Combinations, ICAS 84–1. In this study, several questions relevant to the viscous transonic cascade problem are posed and answered by considering simple flow situations.

These questions focus upon spatial differencing, specification of boundary conditions and use of artificial dissipation in flows containing shock waves. In regard to the first of these problems, the model problem clearly shows that converged solutions.

Please use this form to inquire about the full-text for the document if it is not available in the record details section. To check the document record for full-text availability, look for the following: NTRS Full-Text: Click to View External Online Source: [URL] Use the questions, comments, and feedback text box below for other inquiries about [ ].Experimental measurements in the inlet of a transonic turbine blade cascade showed unacceptable pitchwise flow nonuniformity.

A three-dimensional, Navier–Stokes computational fluid dynamics (CFD) analysis of the imbedded bellmouth inlet in the facility was performed to identify and eliminate the source of the flow nonuniformity.Flow Conditions Using a Navier-Stokes Solver,” NASA CRLondenberg, W., “Transonic Navier-Stokes Calculations About a 65 degree Delta Wing,” NASA CRLondenberg, W., “Turbulence Model Evaluation for the Prediction of Flows Over a Supercritical Airfoil with Deflected Aileron at High Reynolds Number,” AIAA