HYPERSONIC LAMINAR WAKES AND TRANSITION STUDIES (TASKS 3.1 AND 3.5--REST PROJECT)
Abstract
Results are presented of theoretical and experimental investigations of the flow in the wake of hypersonic vehicles. Nonsimilar solutions of the equations governing the ''far wake'' are obtained and contrasted with similar solutions and with solutions involving the KarmanPohlhausen approach. Numerical examples of the flow field in the wake of ballistic-range and wind-tunnel models and of a flight-size vehicle are presented. A series of ballistic-range experiments 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 mmHg in air. The experimental data is discussed in detail, and the analysis if used to compute and correlate appropriate transition parameters. Based on the correlation, predictions of the location of transition in the wake of a 12-degree half-angle cone at 22.000 ft/sec are made for the altitude range from 200,000 to 100,000 feet. For example, transition is placed at approximately 250, 100, and 20 feet from the apex of a 5-foot cone at altitudes of 200,000, 150,000 and 100,000 feet, respectively, assuming the boundary layer on the cone surface remains laminar.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 25, 1963
- Accession Number
- AD0424433
Entities
People
- A. J. Pallone
- J. Eckerman
- J. I. Erdos