THERMAL PROTECTION OF STRUCTURAL, PROPULSION, AND TEMPERATURE-SENSATIVE MATERIALS FOR HYPERSONIC AND SPACE FLIGHT. PART III. ANALYTICAL STUDIES OF PHENOMENA FOR THERMAL PROTECTION
Abstract
Identifiers: Mass transport cooling. Mass transfer cooling in turbulent boundary layers was studied analytically. For 0 pressure gradient, flat plate flow, the effectiveness of mass addition in reducing heat transfer was less in the turbulent boundary layers than in laminar boundary layers. The cooling phenomenon at axisymmetric stagnation points was studied by introducing air and He through a porous wall. Below certain critical injection rates, experimental heat transfer with air injection agreed with theoretical predictions. For coolant flow rates in excess of certain critical values, heat transfer rates increased and became erratic. The effect of upstream mass injection on downstream heat transfer shows downstream heat transfer increased from mass injection. The 1-magawatt air-stablized arc was operated with a mixing chamber and transition piece, and characterization studies including temperature determinations and calorimetry were performed. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1961
- Accession Number
- AD0267510
Entities
People
- Donald E. Taylor
- William P. Manos