Hypersonic aerodynamics and heat transfer
著者
書誌事項
Hypersonic aerodynamics and heat transfer
Begell, c2014
大学図書館所蔵 全1件
  青森
  岩手
  宮城
  秋田
  山形
  福島
  茨城
  栃木
  群馬
  埼玉
  千葉
  東京
  神奈川
  新潟
  富山
  石川
  福井
  山梨
  長野
  岐阜
  静岡
  愛知
  三重
  滋賀
  京都
  大阪
  兵庫
  奈良
  和歌山
  鳥取
  島根
  岡山
  広島
  山口
  徳島
  香川
  愛媛
  高知
  福岡
  佐賀
  長崎
  熊本
  大分
  宮崎
  鹿児島
  沖縄
  韓国
  中国
  タイ
  イギリス
  ドイツ
  スイス
  フランス
  ベルギー
  オランダ
  スウェーデン
  ノルウェー
  アメリカ
注記
Includes bibliographical references and index
内容説明・目次
内容説明
Presents the results of theoretical and experimental studies of the problems of super/hypersonic flows around the models of real space vehicle configurations such as "Buran"-orbiter, winged cone (airplane-like body), Clipper space vehicle, and the Martian planetary probe. Theoretical analysis is based on solution 2/3D Navier- Stokes equations and their simplified asymptotic models with account for equilibrium and nonequilibrium chemical reactions taking place at the background of relaxation of excited internal energy modes of the particles in the shock layer and on the vehicle surface.
Exact and simple relationships for the transport of species mass and heat are derived from rigorous kinetic theory for multicomponent mixtures of gases and plasma with different diffusion characteristics of the species (governing relations - thermodynamic parameter gradients expressed through the fluxes) as well as velocity slip, temperature and species concentration jumps boundary conditions for the surfaces of finite catalycity in multicomponent chemically and thermally nonequilibrium gas flow.
Phenomenological and kinetic models are developed for heterogeneous catalytic reactions on the thermal protection materials of the space vehicles entering Earth and Mars atmospheres along gliding trajectories. The problem of multicomponent thermally and chemically nonequilibrium air flow in inductively coupled plasma torch and jet flow around the models installed in the facility work section in considered. The possibility to specify catalytic properties of real heat shield coatings are demonstrated using numerical and test values of heat fluxes or surface equilibrium radiation temperatures.
The original iterative/marching method to solve viscous shock layer equations is presented. The method is based on the splitting of the marching component of the pressure gradient onto hyperbolic part and a part that minimizes the elliptic part to a maximum degree that are then subjected to the global iterations procedure. Using splitting of this kind allows the obtaining of the drug and heat transfer coefficients within single or couple global iterations.
The knowledge area connected to development of large computer software for conjugate problem of ballistics, aerodynamics, vehicle heat transfer and thermal strength of constructions of variable mass and shape is developed for all stages of the modern rocket-space vehicle design.
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