HEAT TRANSFER AND TEMPERATURE DISTRIBUTION IN A HEMISPHERICAL NOSE CONE IN HYPERSONIC FLOW
Abstract
On the basis of the comparison between theory and experiment of heat transfer and temperature distribution presented in this report, it is concluded that he simplified method used to predict temperatures within a hemispherical nose cone in a hypersonic flow is satisfactory. The restriction must be made to flows in the Reynolds Number range of from 1 to 5 times 10 to the 6th power, and to stagnation temperatures less than 4000 R. To apply the method it is first necessary to calculate the theoretical heat transfer for the appropriate Reynolds Number. Using the local values of the heat transfer, in conjunction with the transient, one-dimensional heat conduction solution through a spherical shell element, yields the temperature-time history at any point within the body.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1962
- Accession Number
- AD0273837
Entities
People
- Ronald W. Sadler
- S. V. Nardo
Organizations
- New York University Tandon School of Engineering