Abo Bibliothek: Guest
Digitales Portal Digitale Bibliothek eBooks Zeitschriften Referenzen und Berichte Forschungssammlungen
Heat Transfer Research
Impact-faktor: 0.404 5-jähriger Impact-Faktor: 0.8 SJR: 0.264 SNIP: 0.504 CiteScore™: 0.88

ISSN Druckformat: 1064-2285
ISSN Online: 2162-6561

Volumes:
Volumen 50, 2019 Volumen 49, 2018 Volumen 48, 2017 Volumen 47, 2016 Volumen 46, 2015 Volumen 45, 2014 Volumen 44, 2013 Volumen 43, 2012 Volumen 42, 2011 Volumen 41, 2010 Volumen 40, 2009 Volumen 39, 2008 Volumen 38, 2007 Volumen 37, 2006 Volumen 36, 2005 Volumen 35, 2004 Volumen 34, 2003 Volumen 33, 2002 Volumen 32, 2001 Volumen 31, 2000 Volumen 30, 1999 Volumen 29, 1998 Volumen 28, 1997

Heat Transfer Research

DOI: 10.1615/HeatTransRes.v31.i6-8.20
pages 380-387

Numerical Simulation of the Effect of Porous Cooling in Aerodynamic Heating of the Elements of Air Ducts and Surfaces by a Hypersonic Viscous Gas Flow

Alexander Leontiev
Joint Institute for High Temperatures
V. V. Nosatov
N. E. Bauman Moscow State Technical University, Moscow, Russia
G. S. Sadovnikov
N. E. Bauman Moscow State Technical University, Moscow, Russia
D. P. Frolov
Academy of Civil Aviation, St. Petersburg, Russia

ABSTRAKT

Effectiveness of the conception of porous cooling is diagnosed in numerical stimulation of aerodynamic heating of a wall that is caused by interaction of a generated shock wave and a boundary layer developing along the surface in a hypersonic flow past a wall and a blunt wedge. The developed programming complex based on the solution of the system of the Navier-Stokes and Reynolds equations, which in the latter case is closed by two differential equations of a dissipation two-parameter model of turbulence, by the explicit-implicit finite-difference McCormack method is tested in the solution of a classic problem of interaction between an oblique shock wave and a turbulent boundary layer. The results of calculation are compared to the available data of experimental studies. Numerical prediction of flow characteristics and heat transfer showed a substantial decrease in heat transfer in the case of realization of low-intensity gas injection at the most thermally stressed site of the wall.


Articles with similar content:

A NUMERICAL STUDY ON A SUPERSONIC COMPRESSOR CASCADE USING R-ε TURBULENCE CLOSURE
International Heat Transfer Conference 11, Vol.18, 1998, issue
D. J. Song, S. D. Kim, I. K. Chung
Numerical Simulation of the Effect of Porous Cooling of Bodies in Hypersonic Flow
Heat Transfer Research, Vol.33, 2002, issue 1&2
G. S. Sadovnikov, V. V. Nosatov, Alexander Leontiev
Experimental Research of Adiabatic Wall Temperature Influenced by Separated Supersonic Flow
International Heat Transfer Conference 15, Vol.18, 2014, issue
Urii A. Vinogradov, Sergey S. Popovich, Kirill Egorov
EFFECTS OF SURFACE CATALYTICITY ON COMPUTED HEAT TRANSFER OVER A REENTRY VEHICLE
ICHMT DIGITAL LIBRARY ONLINE, Vol.13, 2008, issue
Antonio Viviani, G. Pezzella, Carmine Golia
EXPERIMENTAL INVESTIGATION OF BOUNDARY LAYER STATE ON THE MODEL OF INTEGRATED DESIGN HIGH-SPEED VEHICLE AND ITS IMPACT UPON THE CONVERGENT INTAKE STARTING
TsAGI Science Journal, Vol.49, 2018, issue 6
Ivan Valerievich Nazhimov , Yury Grigorievich Shvalev , Stanislav Sergeevich Alyoshin , Valerii Nikolaevich Golubkin, Anatoliy Aleksandrovich Gubanov, Vadim Alekseevich Talyzin, Valentina Alexandrovna Yakovleva