ASYMMETRIC FLOW AROUND THE FRONTAL PART OF A BODY OF ROTATION BY A SUPERSONIC STREAM OF AN IDEAL OR REAL GAS,
Abstract
A method for calculating a supersonic flow past an asymmetric body of revolution is applied to the case of an airflow in the presence of dissociation and ionization. This approach makes use of the method of integral relations in its first approximation, with interpolation from the body to the shock with respect to two variables. A body-oriented asymmetric coordinate system is employed with origin at the stagnation point. The method makes it possible to calculate the flow over a spherical segment with respect to the angle of attack in the region of the angle of attack in which (1) the velocity on the entire surface of the segment is less than the velocity of sound on the surface and (2) the elliptical zone is adjacent only to a portion of the segment surface. The results of the calculation of the flow of a perfect gas over a disk and a spherical segment are substantiated by available experimental data. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 16, 1968
- Accession Number
- AD0682826
Entities
People
- A. N. Minailos
- I. G. Kozlova
Organizations
- National Air and Space Intelligence Center