SLIP FLOW IN THE LAMINAR BOUNDARY LAYER OVER A FLAT PLATE AT HYPERSONIC SPEEDS
Abstract
First order slip in the boundary layer on a flat plate is obtained by adding on to the no slip solution the normal derivative of the no slip solution multiplied by a suitably small parameter. Although carried out only for the similar solution obtained when the pressure gradient is inversely proportional to the square root of distance along the plate, the method can be extended to non-similar solutions. The cases of hypersonic flow in differing ambient temperature environment were calculated and they indicated the effects of slip to cover a considerable extent of flow for an inch or two downstream of the leading edge. The results were essentially the same as those obtained by Casaccio (J. Aero. Space Sci. 27:319-320, (1960); Republic Aviation Corp. RAC No. 643-100(1959)). It was found that there is a dependence of the coefficients in the slip boundary conditions upon the form of the similarity transformation of the boundary layer equations. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1961
- Accession Number
- AD0257834
Entities
People
- Robert E. Street
Organizations
- University of Washington