Influence of shock wave impinging region on supersonic film cooling-Reference-Cited by-同舟云学术

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Influence of shock wave impinging region on supersonic film cooling

Published:2021-05 Issue:5 Volume:34 Page:452-465
ISSN:1000-9361
Container-title:Chinese Journal of Aeronautics
language:en
Short-container-title:Chinese Journal of Aeronautics

Author:

SUN Xiaokai,NI Hang,PENG Wei,JIANG Peixue,ZHU Yinhai

Funder

Science Fund for Creative Research Groups

National Science and Technology Major Project

Publisher

Elsevier BV

Subject

Mechanical Engineering,Aerospace Engineering

Reference42 articles.

1. Supersonic film cooling;Bass,1990

2. Experimental study on the full-coverage film cooling of fan-shaped holes with a constant exit width;Wei;Int J Heat Mass Transf,2019

3. Numerical assessment of round-to-slot film cooling performances on a turbine blade under engine representative conditions;Zhu;Int Commun Heat Mass Transf,2019

4. Numerical modeling and analysis of grooved surface applied to film cooling;Guo;J Bionic Eng,2011

5. Investigations on the film cooling of counter-inclined film-hole row structures for turbine vane leading edge;Liu;Int J Turbo Jet Engines,2018

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1. An experimental study of supersonic conical cooling films subjected to different ratios of static pressure;Physics of Fluids;2024-08-01

2. Research progress in aero-optical effects of supersonic turbulent shear layers;Progress in Aerospace Sciences;2024-04

3. Numerical Study of Discrete Hole Supersonic Film Cooling with Shock Generator;Journal of Aerospace Engineering;2024-03

4. Flow evolution of mixed layer on convex curvature wall under hypersonic conditions;Acta Physica Sinica;2024

5. Effect of Geometric Parameters on Steady-State Supersonic Film Cooling of the Basic Conical Rocket Nozzle;Lecture Notes in Mechanical Engineering;2024

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