Boundary-layer transition on a cone and flat plate at Mach 3.5

[1]  I. E. Beckwith,et al.  Design and fabrication requirements for low-noise supersonic/hypersonic wind tunnels , 1988 .

[2]  A. R. Wazzan,et al.  Tollmien-Schlichting waves and transition: Heated and Adiabatic Wedge Flows with Application to Bodies of Revolution☆ , 1979 .

[3]  Kenneth F Stetson.  Effect of Bluntness and Angle of Attack on Boundary Layer Transition on Cones and Biconic Configurations , 1979 .

[4]  I. E. Beckwith,et al.  Nozzle optimization study for quiet supersonic wind tunnels , 1984 .

[5]  A. Smith,et al.  Determination of spatial amplification factors and their applicationto predicting transition , 1969 .

[6]  Donald Coles,et al.  Measurements of Turbulent Friction on a Smooth Flat Plate in Supersonic Flow , 1954 .

[7]  C. J. Schueler,et al.  Radiated aerodynamic noise effects on boundary-layer transition in supersonic and hypersonic wind tunnels. , 1969 .

[8]  G. Rushton,et al.  Shock tunnel investigation of boundary-layer transition at M equals 5.5. , 1966 .

[9]  I. E. Beckwith,et al.  Design requirements for the NASA Langley supersonic low-disturbance wind tunnel , 1986 .

[10]  M. R. Malik,et al.  Effect of curvature on three-dimensional boundary-layer stability , 1985 .

[11]  S. Pate,et al.  Measurements and Correlations of Transition Reynolds Numbers on Sharp Slender Cones at High Speeds , 1971 .

[12]  M. R. Malik,et al.  Instability and transition in rotating disk flow , 1981 .

[13]  L. Mack.  Linear Stability Theory and the Problem of Supersonic Boundary- Layer Transition , 1975 .

[14]  Mujeeb R. Malik,et al.  Prediction and control of transition in hypersonic boundary layers , 1987 .