NUMERICAL CALCULATIONS OF THE FLOW AROUND A FLARED CONE (CHISLENNII RASCHET OBTAKANIYA STUPENCHATOVO KONUSA),
Abstract
A method is presented for the numerical computation of the flow near a sharp nosed right circular cone-flare immersed in a supersonic ideal gas flow. It is assumed that the flow is uniform, the free-stream velocity vector is parallel to the axis of the body, and conditions are such that the conical nose shock is attached. It is further assumed that the flare (second cone) angle is greater than the cone angle, so that a curvilinear shock originating from the intersection of the cone-flare is generated. At some distance from the body both shocks intersect. In the region bounded by the shocks and the cone, the flow is conical and solutions of conic flows are given in tabular form. Beyond the curvilinear shock the flow becomes vortical and the calculating of it presents many difficulties. The vortical flow field, with the exception of the neighborhood of cone-flare intersection, is calculated by the method of characteristics. For the determination of the flow field near the intersection the results of an approximate theory are utilized. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1965
- Accession Number
- AD0627881
Entities
People
- G. S. Roslyakov
- N. V. Drozdov
Organizations
- RAND Corporation