EXPERIMENTAL PRESSURE, TEMPERATURE, AND STRAIN MEASUREMENTS ON ABLATING HEMISPHERICAL NOSE CONES IN HYPERSONIC FLOW. TEST SERIES 2
Abstract
The results of pressure, temperature and strain measurements on three hemispherical nose cones tested and ablated in a hypersonic tunnel are presented. The shrouded model technique was used in all tests. Wind tunnel stagnation pressure was maintained at a normal value, Stresses, Measurement, Hypersonic wind tunnels.) (Wind tunnel models, Aluminum alloys, Surface area, Ablation, Guided missile noses.) (Experimental data, Tables, Photographs.) The results of pressure, temperature and strain measurements on three hemispherical nose cones tested and ablated in a hypersonic tunnel are presented. The shrouded model technique was used in all tests. Wind tunnel stagnation pressure was maintained at a nominal value of 150 psia, and stagnation temperatures varied from 1650 R to 1900 R. The test conditions correspond to Mach numbers in the range of 15 to 20, at altitudes of from 60,000 to 70,000 ft. All three models were fabricated from cast aluminum alloy 356 T- 6, and all models had outside diameters of 7-3/4 inches. Two models were 1-in. thick, and the third had a 1/2-in. thickness. Ablation of the surface material was allowed to occur in all tests. A complete presentation of the data is given in the form of tables, graphs, and photographs.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1961
- Accession Number
- AD0264410
Entities
People
- Burton Erickson
- Joseph Kempner
- S. V. Nardo
Organizations
- New York University Tandon School of Engineering