HYPERSONIC LAMINAR WAKES AND TRANSITION STUDIES (TASKS 3.1 AND 3.5 - REST PROJECT),
Abstract
This report presents the results of theoretical and experimental investigations of the flow in the wake of slender hypersonic vehicles. Non similar solutions of the equations governing the far wake are obtained and contrasted with similar solutions and with solutions involving the Karman-Pohlhausen approach. Several numerical examples of the flow field in the wake generated by ballistic range models and by flight vehicles are presented. A series of ballistic range ex periments with conical models of 10, 15, and 27-1/2-degree half-angles are described. The model velocity ranges between 4,000 and 17,000 ft/sec with range pressures varying from 15 to 380 mm of Hg in air. The experimental data is discussed in detail and the analysis is used to compute and correlate appropriate transition parameters. Based on the correlation, transition in the wake of a 5-foot 12-degree half-angle cone at 22, 000 ft/sec is predicted to occur at ap proximately 20, 100, and 250 feet from the apex of the cone at altitudes of 100,000, 150,000 and 200,000 feet respectively. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 14, 1963
- Accession Number
- AD0413533
Entities
People
- A.j. Pallone
- J. Eckerman
- J.i. Erdos
- W. Mckay