Computational Study on Hysteretic Inlet Buzz Characteristics Under Varying Mass Flow Conditions-Reference-Cited by-同舟云学术

Computational Study on Hysteretic Inlet Buzz Characteristics Under Varying Mass Flow Conditions

Published:2014-07 Issue:7 Volume:52 Page:1357-1373
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Hong Wooram¹,Kim Chongam²

Affiliation:

1. Samsung Electronics Inc., Suwon 443-803, Republic of Korea

2. Department of Aerospace Engineering, Institute of Advanced Aerospace Technology, Interdisciplinary Program in Computational Science & Technology, Seoul National University, Seoul 151-742, Republic of Korea

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/1.J052481

Reference27 articles.

1. OswatitschK. “Pressure Recovery in Missiles with Reaction Propulsion at High Supersonic Speeds (the Efficiency of Shock Diffusers),” NACA TM-1140, 1947.

2. Supersonic Diffuser Instability

3. FerriA.NucciR. M. “The Origin of Aerodynamic Instability of Supersonic Inlets at Subcritical Conditions,” NACA RM-L50K30, Jan. 1951.

4. NagashimaT.ObokataT.AsanumaT. “Experiment of Supersonic Air Intake Buzz,” Inst. of Space and Aeronautical Science of Tokyo, Rept. 481, Tokyo, May 1972.

5. Numerical Simulation of Near-Critical and Unsteady, Subcritical Inlet Flow

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