Solution is obtained by dividing flowfield into three subregions; vortical outer flow, resulting from inviscid expansion of boundary layer, is solved by method-of-characteristics; thin viscous layer above dividing streamline is treated with modified Oseen solution of boundary-layer equations; recirculation region is solved by finite-difference representation of full Navier-Stokes equations; iteration scheme is developed and shown to yield converged solutions of coupled flowfield; complete solutions up to rear stagnation point are found to be possible for range of base pressures.
New theoretical solution of laminar, hypersonic near Wake
AIAA J
AIAA Journal ; 5 , n 12
1967
8 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Analysis of laminar near-wake hypersonic flows
AIAA | 1995
|Analysis of Laminar Near-Wake Hypersonic Flows
Online Contents | 1995
|