نتایج جستجو برای: Aerodynamic heating

تعداد نتایج: 66424  

Journal: :علوم و فناوری فضایی 0
s. ghasemloo s. noori

in this paper, an approximate axisymmetric method is developed which can reliably calculate fully viscous hypersonic flow over blunt-nosed bodies. in this method, a maslen’s second-order pressure expression is used instead of the normal momentum equation. the combination of maslen’s second-order pressure expression and viscous shock layer equations is developed to accurately and efficiently com...

Journal: :علوم و فناوری فضایی 0
s. a. hosseini s. noori

in the present work, an engineering method is developed to predict laminar and turbulent heating-rate solutions for blunt reentry spacecraft at hypersonic conditions. the calculation of aerodynamic heating around blunt bodies requires alternative solution of inviscid flow field around the hypersonic bodies. in this paper, the procedure is of an inverse nature, that is, a shock wave is assumed a...

Journal: :Quarterly of Applied Mathematics 1951

Journal: :Journal of the Japan Society for Aeronautical and Space Sciences 1990

Journal: :Physics Today 2021

For the last quarter of 20th century, Concorde airliners and other supersonic aircraft shuttled wealthy passengers between North America Europe at speeds up to 600 m/s (about 1350 mph). The planes were retired in 2003. They had grown prohibitively expensive worried passengers, who couldn’t help but notice that planes’ windows too hot touch.Today, however, several airlines have plans reinstate j...

Journal: :National Science Review 2018

2012

A parallel computational fluid dynamics code has been developed for the study of aerodynamic heating problem in hypersonic flows. The code employs the 3D Navier-Stokes equations as the basic governing equations to simulate the laminar hypersonic flow. The cell centered finite volume method based on structured grid is applied for spatial discretization. The AUSMPW+ scheme is used for the invisci...

2012
Yisheng Rong Jian Sun Weiqiang Liu Renjun Zhan

A CFD study on heat flux reduction in hypersonic flow with opposing jet has been conducted. Flowfield parameters, reattachment point position, surface pressure distributions and heat flux distributions are obtained and validated with experiments. The physical mechanism of heat reduction has been analyzed. When the opposing jet blows, the freestream is blocked off, flows to the edges and not int...

Journal: :The Journal of the Japan Society of Aeronautical Engineering 1967

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