Affiliation:
1. Moscow Institute of Physics and Technology
2. University of Arizona
Publisher
American Institute of Aeronautics and Astronautics
Reference20 articles.
1. Shock tunnel investigation of boundary-layer transition at M equals 5.5.
2. Effect of bluntness and angle of attack on boundary layer transition on cones and biconic configurations
3. Brinich, P. F. "Effects of Leading-Edge Geometry on Boundary Layer Transition at Mach3.1," NACATN-3659, March1956.
4. Brinich, P. F., and Sands, N. "Effects of Bluntness on Transition for a Cone and a Hollow Cylinder at Mach 3.1," NACA TN-3679, May1957.
5. Laminar boundary-layer growth on slightly blunted cones at hypersonic speeds
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