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Calculation of afterbody flows with a composite velocity formulationA recently developed technique for numerical solution of the Navier-Stokes equations for subsonic, laminar flows is investigated. It is extended here to allow for the computation of transonic and turbulent flows. The basic approach involves a multiplicative composite of the appropriate velocity representations for the inviscid and viscous flow regions. The resulting equations are structured so that far from the surface of the body the momentum equations lead to the Bernoulli equation for the pressure, while the continuity equation reduces to the familiar potential equation. Close to the body surface, the governing equations and solution techniques are characteristic of those describing interacting boundary layers. The velocity components are computed with a coupled strongly implicity procedure. For transonic flows the artificial compressibility method is used to treat supersonic regions. Calculations are made for both laminar and turbulent flows over axisymmetric afterbody configurations. Present results compare favorably with other numerical solutions and/or experimental data.
Document ID
19830055997
Document Type
Conference Paper
Authors
Swanson, R. C. (NASA Langley Research Center Theoretical Aerodynamics Branch, Hampton, VA, United States)
Rubin, S. G. (NASA Langley Research Center Hampton, VA, United States)
Khosla, P. K. (Cincinnati, University Cincinnati, OH, United States)
Date Acquired
August 11, 2013
Publication Date
July 1, 1983
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 83-1736
Funding Number(s)
CONTRACT_GRANT: NAG1-8
Distribution Limits
Public
Copyright
Other