On Reflection of Shock Waves from Boundary Layers
Abstract
Measurements of the reflection characteristics of shock waves from a flat surface with a laminar and turbulent boundary layer are presented. The investigations were carried out at Mach numbers from about 1.3 to 1.5 and a Reynolds number of 0.9 x 10(exp 6). The difference in the shock-wave interaction with laminar and turbulent boundary layers, first found in transonic flow, is confirmed and investigated in detail for supersonic flow. The relative upstream influence of a shock wave impinging on a given boundary layer has been measured for both laminar and turbulent layers. The upstream influence of a shock wave in the laminar layer is found to be of the order of 50 boundry-layer thicknesses as compared with about 5 in the turbulent case. Separation almost always occurs in the laminar boundary layer. The separation is restricted to a region of finite extent upstream of the shock wave. In the turbulent case no separation was found. A model of the flow near the point of impingement of the shock wave on the boundary layer is given for both cases. The difference between impulse-type and step-type shock waves is discussed and their interaction with the boundary layer is compared. Some general considerations on the experimental production of shock waves from wedges and cones are presented, as well as a discussion of boundary layer in supersonic flow. A few examples of reflection of shock waves from supersonic shear layers are also presented.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1951
- Accession Number
- ADA382023
Entities
People
- A. Roshko
- H. W. Liepmann
- S. Dhawan
Organizations
- California Institute of Technology