Predictions of Aerodynamic Heating on Tactical Missile Domes
Abstract
The laminar heating on the hemisphere-cylinder configuration has been calculated using various predictive techniques in the Mach number range of one to five. The accuracy of these approximate results is assessed using the Cebeci-Smith finite difference code as a standard. A new procedure is suggested which is based on the consistent use of the Kays' semi-empirical formulas, and it appears to offer very accurate predictions of aerodynamic heating on the configuration under study. A similar comparison on the turbulent heating predictions is also briefly discussed. In the transition region, a new approach of aerodynamic heating calculation based on the so-called 'spot theory' is introduced, and some results are presented and discussed. Transient heat conduction inside the missile structure is studied using a new integral technique.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 25, 1979
- Accession Number
- ADA073217
Entities
People
- T. F. Zien
- W. C. Ragsdale
Organizations
- Naval Ordnance Laboratory