Direct Numerical Simulation of Foreign-Gas Film Cooling in Supersonic Boundary-Layer Flow
Author:
Affiliation:
1. University of Stuttgart, D-70550 Stuttgart, Germany
Funder
Deutsche Forschungsgemeinschaft
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.J055115
Reference39 articles.
1. Influence of injectant Mach number and temperature on supersonic film cooling
2. Experimental and Numerical Study of Supersonic Film Cooling
3. Influence of Shock Waves on Supersonic Film Cooling
4. Numerical Simulation of Coolant Variation in Laminar Supersonic Film Cooling
5. Numerical simulation of cooling gas injection using adaptive multiresolution techniques
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