The Calculation of Adiabatic Laminar Boundary Layer Shock Wave Interactions in Axi-Symmetric Flow. Part II. Hollow Cylinder Flare Bodies with Spin.
Final scientific rept. 1 May 70-30 Apr 71,
VON KARMAN INST FOR FLUID DYNAMICS RHODE-SAINT-GENESE (BELGIUM)
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The report is concerned with developing a theoretical calculation method for the three-dimensional interaction between a laminar boundary layer and a shock wave, in the case when a constant transverse velocity is imposed, parallel to the shock plane. The phenomenon is studied on an adiabatic axi-symmetric body consisting of a hollow circular cylinder with a flare. The transverse velocity is generated by the rotation of the body about its axis of symmetry which is aligned in the main flow direction. The calculation procedure is derived from the two-dimensional integral method of Lees and Reeves. The required relationships between boundary layer integral properties are obtained from similar solutions of compressible axial flow on a rotating cylinder.
- Fluid Mechanics