Hypersonic and High Temperature Gas Dynamics

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Since it is often difficult to determine the fluid temperature gradient at the wall, we use conservation of energy at the wall interface assuming there is not mechanism for heat storage at the interface to write:.


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That is, h q is often determined experimentally, so measure the magnitude of qdot doubleprime wall and set up. In applications, however, h q is usually determined either numerically from solving the boundary layer problem, or h q is found from Nusselt number heat transfer correlations, in the form:. The fact that the boundary layer at high speed can be quite hot means that the boundary layer fluid density can be quite low; hence, the boundary layer spreads outward from the wall, getting quite thick.

Anderson notes that the boundary layer thickness grows as. The thick boundary layer can significantly modify or force changes to the outer inviscid flow, in particular, the inviscid pressure distribution over the body. See Fig. Of course, the coupling can be two-way, that the outer pressure distribution can affect the boundary layer. So the problem can be non-linear. This is especially true if the boundary layer merges with the outer shock wave. Question: What is the limit for the contraction ratio between A 2 and A 4? L5D20, May Item Information Condition:.

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Hypersonic and High Temperature Gas Dynamics McgrawHill Series in Aeronautical and Aerospa

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Item specifics Condition: Brand New: A new, unread, unused book in perfect condition with no missing or damaged pages. See all condition definitions - opens in a new window or tab Read more about the condition. About this product. Eighteen chapters are presented in sections on inviscid hypersonic flow, viscous hypersonic flow, and high-temperature gas dynamics. The only background assumed by the text is a basic knowledge of undergraduate fluid dynamics, including an introductory course on compressible flow.

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Hypersonic and High Temperature Gas Dynamics

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