Arc-Tunnel Evaluation of Some Ablative Heat Shield Materials for the X-15-2.
Abstract
Fourteen ablation materials have been investigated at test conditions simulating the heating predicted for the X-15-2 research aircraft. Twenty-seven wedge-shaped models with a leading-edge radius similar to the X-15-2 wing and horizontal stabilizer leading edges were tested in the 2-inch supersonic arc tunnel at the Langley Research Center. The ablation materials were exposed to the heating conditions which will occur on the X-15-2 leading edges and fuselage areas at an altitude of 105,000 feet (32 kilometers) and at Mach number 8. The results presented include back surface temperature response at several locations on the models and photographs of the models before and after testing.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1967
- Accession Number
- ADA307162
Entities
People
- Andrew J. Chapman
- Marvin B. Dow
Organizations
- Langley Research Center