Effect of wall temperature on a supersonic turbulent boundary layer
Author:
Affiliation:
1. Ford Aerospace and Communications Corp., Newport Beach, Calif.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.7570
Reference23 articles.
1. ^aderman, A. J. and Demetriades, A. "Final Technical Report; Investigation of the Structure of a Cooled Wall Turbulent Supersonic Boundary Layer," Ford Aerospace and Communications Corp., Aeronutronic Division, Publication No.U-6370,Oct. 1977.
2. Evaluation of the turbulent transport terms for a two-dimensional nozzle wall boundary-layer flow at Mach 5 and with pressure gradient, heat transfer and upstream effects
3. Wall cooling effects on hypersonic transitional/turbulent boundary layers at high Reynolds numbers
4. Velocity-Temperature Relations in Turbulent Boundary Layers with Nonunity Prandtl Numbers
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