ON THE USE OF THE SHOCK LAYER APPROXIMATION IN THE INVERSE HYPERSONIC BLUNT BODY PROBLEM,
Abstract
The usefulness of the shock-layer approximation as a method of attack to the hypersonic blunt body problem is studied. Mainly the inverse problems of axisymmetric inviscid flow of a calorically perfect gas (in which the shock geometry is given) are discussed. Methods which are consistent with approximations based on a high shock compression ratio (but modified to take into account the contribution of the tangential pressure gradient and some other second order terms) are proposed. Good agreement in body shape and streamlines with other more exact (numerical) solutions is shown not only for specific heat ratios as high as gamma = 5/3 and 2, but also for stagnation regions of very blunt configurations, for which the standard shock-layer theory completely fails. Analytic forms of the pressure field, body and streamline geometries are developed for the sonic family shocks (of arbitrary degree of oblateness and eccentricity) in stagnation regions. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1965
- Accession Number
- AD0630780
Entities
People
- G. A. Gaitatzes
- H. K. Cheng
Organizations
- Douglas