Supersonic Flow about Right circular Cones at Zero Yaw in Air at Thermodynamic Equilibrium. Part 2. Tables of Data
Abstract
Part I (AD0468284) of this report is an analysis of the inviscid flow fields for air in chemical equilibrium about right circular cones at zero yaw. Parts II and III present, in tabular form, the results of the calculation of real gas supersonic flow fields about right circular cones at zero angle of yaw upon which the correlation analysis in Part I is based. The calculations were performed by a numerical integration of the conical flow equations written in terms of a single geometric parameter, the ray angle eta; thus, the results are independent of body size. Flow properties are given along rays which are defined by 10 equal angular increments between the shock and cone surface. Numerical calculations were performed utilizing the Picatinny Arsenal IBM 709/90/94 Conical Flow Field Program. Results are obtained for cone semi-angles from 2.5 degrees to 50 degrees, altitudes from 0 to 200,000 ft, and Mach numbers from 3 to 40, excluding those which result in a detached shock or are well within the ideal gas regime.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1964
- Accession Number
- AD0628539
Entities
People
- Henry E. Hudgins
Organizations
- Picatinny Arsenal