Effect of Adverse Pressure Gradient on Film Cooling Effectiveness
Author:
Affiliation:
1. New York University, New York, N.Y.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.49323
Reference6 articles.
1. An experimental investigation of turbulent slot injection at Mach 6
2. A note on the use of a boundary-layer model for correlating film-cooling data
3. Gaseous film cooling at various degrees of hot-gas acceleration and turbulence levels
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