NDLI: Transonic navier-stokes solutions of three-dimensional afterbody flows

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Transonic navier-stokes solutions of three-dimensional afterbody flows

Content Provider	NASA Technical Reports Server (NTRS)
Author	Compton II, William B. Thomas, James L. Mason, Mary L. Abeyounis, William K.
Copyright Year	1989
Description	The performance of a three-dimensional Navier-Stokes solution technique in predicting the transonic flow past a nonaxisymmetric nozzle was investigated. The investigation was conducted at free-stream Mach numbers ranging from 0.60 to 0.94 and an angle of attack of 0 degrees. The numerical solution procedure employs the three-dimensional, unsteady, Reynolds-averaged Navier-Stokes equations written in strong conservation form, a thin layer assumption, and the Baldwin-Lomax turbulence model. The equations are solved by using the finite-volume principle in conjunction with an approximately factored upwind-biased numerical algorithm. In the numerical procedure, the jet exhaust is represented by a solid sting. Wind-tunnel data with the jet exhaust simulated by high pressure air were also obtained to compare with the numerical calculations.
File Size	5084263
Page Count	60
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19890014062
Archival Resource Key	ark:/13960/t3gx96t5b
Language	English
Publisher Date	1989-07-01
Access Restriction	Open
Subject Keyword	Aerodynamics Navier-stokes Equation Transonic Flow Algorithms Nozzle Flow Turbulence Models Afterbodies Wind Tunnel Tests Finite Volume Method Angle of Attack Jet Exhaust Three Dimensional Models Axisymmetric Bodies Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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