Transition of Hypersonic Boundary Layer-Reference-Cited by-同舟云学术

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Transition of Hypersonic Boundary Layer

Published:1965 Issue:2 Volume:8 Page:211
ISSN:0031-9171
Container-title:Physics of Fluids
language:en
Short-container-title:Phys. Fluids

Author:

Nagamatsu H. T.,Graber B. C.,Sheer R. E.

Publisher

AIP Publishing

Subject

General Engineering

Reference32 articles.

1. Hypersonic Shock Tunnel

2. H. T. Nagamatsu and R. E. Sheer, Jr., General Electric Research Laboratory Report 64-RL-3622C (1964).

3. G. B. Schubauer and H. K. Skramstad, NACA Report 909 (1948).

4. The three-dimensional nature of boundary-layer instability

5. P. F. Brinich, and N. S. Diaconis, NACA Technical Note 2742 (1952).

Cited by 7 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Wall cooling effects on hypersonic boundary layer transition, M(1) =7.5 - 15;4th Joint Fluid Mechanics, Plasma Dynamics and Lasers Conference;1986-05-12

2. Critical layer concept relative to hypersonic boundary layer stability;23rd Aerospace Sciences Meeting;1985-01-14

3. Laminar, transition, and turbulent boundary- layer characteristic with favorable pressure gradient M sub 1 equals 9.6;Journal of Aircraft;1971-03

4. Boundary-layer transition on sharp cones at hypersonic Mach numbers.;AIAA Journal;1968-03

5. Hypersonic laminar boundary-layer transition on 8-foot-long, 10 deg cone, M sub 1 equals 9.1-16.;AIAA Journal;1967-07

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