Analysis of Laminar Boundary Layers on Right Circular Cones at Angle of Attack, Including Streamline-Swallowing Effects
Final rept. Sep 1970-Apr 1972
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A method has been developed for treating the three-dimensional compressible laminar boundary-layer equations for a right circular cone at angle of attack in supersonic and hypersonic flow. Swallowing by the boundary layer of the inviscid entropy layer streamline swallowing has been treated by means of a mass-flow balance between the inviscid and viscous flowfields. The boundary- layer equations between the inviscid and viscous flowfields. The boundary-layer equations were developed in a general Crocco-variables form. A finite- difference technique was formulated for solving the governing equations and treating the streamline-swallowing phenomenon. The resulting second-order difference equations are solved in an iteration scheme.
- Fluid Mechanics