Calculation of the Laminar Viscous Shock Layer on a Blunt Biconic Body at Incidence to Supersonic and Hypersonic Flow
Abstract
A fully viscous shock layer computation method developed by others to treat laminar flow over a sharp cone at incidence to a supersonic or hypersonic free stream has been extended to consider the case of flow over a blunt biconic configuration at angle of attack. The basic method treats the flow between the body surface and the bow shock wave by one set of equations which are valid in both the viscous and inviscid flow regions. A description is given of the computational methods used, particularly the method developed to treat the viscous shock layer over the spherical nose and the method used to take data from the end of the forecone solution to provide initial data for starting the aft-cone solution. Results from calculations which have been performed using the method developed in this investigation are compared with results from boundary- layer and inviscid flow calculations and with experimental data. The present technique is validated by the good agreement between the computed data and experimental data. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1976
- Accession Number
- ADA033225
Entities
People
- Arloe W. Mayne Jr.
Organizations
- Arnold Engineering Development Complex