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Numerical solutions of the Navier-Stokes equations for transonic afterbody flowsThe time dependent Navier-Stokes equations in mass averaged variables are solved for transonic flow over axisymmetric boattail plume simulator configurations. Numerical solution of these equations is accomplished with the unsplit explict finite difference algorithm of MacCormack. A grid subcycling procedure and computer code vectorization are used to improve computational efficiency. The two layer algebraic turbulence models of Cebeci-Smith and Baldwin-Lomax are employed for investigating turbulence closure. Two relaxation models based on these baseline models are also considered. Results in the form of surface pressure distribution for three different circular arc boattails at two free stream Mach numbers are compared with experimental data. The pressures in the recirculating flow region for all separated cases are poorly predicted with the baseline turbulence models. Significant improvements in the predictions are usually obtained by using the relaxation models.
Document ID
19810005408
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Swanson, R. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1784
L-13826
Report Number: NASA-TP-1784
Report Number: L-13826
Accession Number
81N13919
Funding Number(s)
PROJECT: RTOP 505-32-13-11
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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