Supersonic Combustor Insulation Ablation Analysis and Tests,
Abstract
The design of passively cooled, hypersonic tactical missiles poses many severe structural problems whose solutions are beyond the current state-of-the-art. Specifically, the heating conditions in the supersonic combustor of such a missile approach those in the throat section of rocket motors but are more damaging to most materials because the flow is oxidizing rather than reducing. Carbon-carbon materials are being considered for the supersonic combustor wall structure because they have attractive strength-weight characteristics at elevated temperatures. Since these materials which form an oxidation resistant layer are also being considered. In order to design such a combustor, the designer must be able to accurately predict the erosion rate of candidate materials so that a realistic balance can be achieved between weight and performance. This paper addresses the problem of thermochemical erosion of graphitic materials, the development of procedures for the analytical prediction of these erosion rates in a combustor environment, and experimental procedures used to validate the analytical model and evaluate candidate combustor liner materials. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- May 14, 1981
- Accession Number
- ADA111789
Entities
People
- Harold G. Fox
- Robb W. Newman
Organizations
- Johns Hopkins University