Unstart/Restart Boundary Broadening Method for a Two-Dimensional Supersonic Variable Inlet Based on a Distributed Bleed System-Reference-Cited by-同舟云学术

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Unstart/Restart Boundary Broadening Method for a Two-Dimensional Supersonic Variable Inlet Based on a Distributed Bleed System

Published:2023-01 Issue:1 Volume:36 Page:
ISSN:0893-1321
Container-title:Journal of Aerospace Engineering
language:en
Short-container-title:J. Aerosp. Eng.

Author:

Jin Yi¹,Zhang Yue²,Tan Hui-jun³,Yu Hang¹

Affiliation:

1. Ph.D. Candidate, College of Energy and Power Engineering, Nanjing Univ. of Aeronautics and Astronautics, No. 29, Yudao St., Nanjing 210016, People’s Republic of China.

2. Professor, College of Energy and Power Engineering, Nanjing Univ. of Aeronautics and Astronautics, No. 29, Yudao St., Nanjing 210016, People’s Republic of China (corresponding author).

3. Professor, College of Energy and Power Engineering, Nanjing Univ. of Aeronautics and Astronautics, No. 29, Yudao St., Nanjing 210016, People’s Republic of China.

Publisher

American Society of Civil Engineers (ASCE)

Subject

Mechanical Engineering,Aerospace Engineering,General Materials Science,Civil and Structural Engineering

Link

https://ascelibrary.org/doi/pdf/10.1061/JAEEEZ.ASENG-4615

Reference40 articles.

1. Shock Wave–Boundary-Layer Interactions

2. Benson D. B. T. I. P. Shih and D. O. Davis. 2003. “CFD simulations of an axisymmetric mixed-compression inlet with bleed through discrete holes.” In Proc. 4th ASME/FED and JSME 2003 Joint Fluids Conf. Reston VA: ASME.

3. External-Compression Supersonic Inlet Free from Violent Buzz

4. Effects of Optimized Bleed System on Supersonic Inlet Performance and Buzz

5. Curran, E. T., and S. N. B. Murthy. 2001. Scramjet propulsion. Reston, VA: AIAA Education Series.

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