Exploration of Upstream Influence and the Role of Shock Generator Geometry in Shock Wave/Transitional Boundary Layer Interactions at Mach 1.8 Edge Conditions-Reference-Cited by-同舟云学术

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Exploration of Upstream Influence and the Role of Shock Generator Geometry in Shock Wave/Transitional Boundary Layer Interactions at Mach 1.8 Edge Conditions

Published:2020-06-08 Issue: Volume: Page:
ISSN:
Container-title:AIAA AVIATION 2020 FORUM
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Author:

Lash E. Lara¹,Gragston Mark¹,McDaniel Zachary²,Kreth Phillip A.¹,Schmisseur John D.¹

Affiliation:

1. University of Tennessee, Tullahoma

2. Purdue University

Publisher

American Institute of Aeronautics and Astronautics

Reference35 articles.

1. A review of aerothermal problems associated with hypersonic flight

2. Progress in shock wave/boundary layer interactions

3. Effect of Transition on Three-Dimensional Shock- Wave/Boundary-Layer Interaction

4. Exploratory Experimental Study of Transitional Shock Wave Boundary Layer Interactions

Cited by 2 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. Modal Analysis of Cylinder-Induced Transitional Shock-Wave/Boundary-Layer Interaction Unsteadiness;AIAA Journal;2022-05

2. Velocity, Mach Number, and Static Temperature Measurements in Supersonic Flows with 10 kHz Laser-Induced Schliere Anemometry;AIAA SCITECH 2022 Forum;2022-01-03

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