Stilla, J. (1994) Engineering Transition Prediction of a Hypersonic Axisymmetric Boundary Layer. Journal of Aircraft, pp. 1358-1364.
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for the design of future hypersonic aerospace planes the estimation of maximum heat loads plays an important role. It especially depends on boundary-layer transition for which engineering tools are required at the present time an estimation of transition location in hyper-sonic flow still has to rely on either empirical correlations based on mean-flow properties, or on local, linear stability analysis in conjunction with the e**N method. In any case,a laminar, steady meanflow has to be computed. Each modification of the design requires repeated transition pre- diction and, therefore, repeated computation of laminar, steady mean flows. Because solutions of the full Navier-Stokes equations are verytime consuming, and therefore expensive, one has to choose an approp-riate approximation of these equations. Two common approximations are the parabolized Navier-Stokes equations (PNS) and the thin-layer Navier-Stokes equations (TLNS).
|Title:||Engineering Transition Prediction of a Hypersonic Axisymmetric Boundary Layer|
|Journal or Publication Title:||Journal of Aircraft|
|In ISI Web of Science:||Yes|
|Page Range:||pp. 1358-1364|
|Series Name:||Vol. 31 No.6|
|Keywords:||hypersonic boundarz layers, blunt core, second-order boundarylayer theory, linear local stability analysis, entropy layer|
|HGF - Research field:||UNSPECIFIED|
|HGF - Program:||Space (old)|
|HGF - Program Themes:||W RP - Raumtransport|
|DLR - Research area:||UNSPECIFIED|
|DLR - Program:||W RP - Raumtransport|
|DLR - Research theme (Project):||W - Grundlagen Raumtransport - Anlagen und Messtechnik (old)|
|Location:||Köln-Porz , Braunschweig , Göttingen|
|Institutes and Institutions:||Institute of Aerodynamics and Flow Technology > Institut für Entwurfsaerodynamik|
|Deposited By:||elib DLR-Beauftragter|
|Deposited On:||03 Apr 2006|
|Last Modified:||27 Apr 2009 10:05|
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