THE NON-SIMILAR BOUNDARY LAYER WITH BLOWING,
Abstract
A generalized method is proposed for the numerical and analytical solution of non-similar boundary layer flows with fluid injection. For a given mass injection distribution and external pressure gradient, solutions can be obtained which do not depend on the magnitude of the injected flow rate. Instead, variations in the magnitude of the injected flow are associated with variations in a transformed tangential coordinate. The method is used to generalize a previously obtained numerical solution for the incompressible boundary layer flow over a flat plate with uniform mass injection to the compressible case, and to obtain a solution for the strong interaction of a hypersonic inviscid flow with the boundary layer on a flat plate with uniform mass injection. Numerical results in which the wall temperature is the only parameter are given for the latter case. It is shown that the injected mass flow tends to increase the induced pressure and displacement thickness, and to decrease the heat transfer and wall shear. The wall temperature has a significant effect on the dimensionless pressure and displacement thickness, and a smaller but noticeable effect on the dimensionless heat transfer and shear. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1968
- Accession Number
- AD0666913
Entities
People
- William S. King
Organizations
- The Aerospace Corporation