INVESTIGATION OF TURBULENT HEAT TRANSFER AT HYPERSONIC SPEEDS. VOLUME 1. ANALYTICAL METHODS
Abstract
The report presents a combined analytical and experimental investigation of turbulent heat transfer on basic and composite configurations at hypersonic speeds. The analytical results are presented in Volume 1. Two analytical approaches are presented: the rho sub r mu sub r method and the turbulent nonsimilar boundary layer method. The rho sub r mu sub r method, which is derived from the boundary layer momentum and energy integral equations, is recommended for predicting turbulent heating rates. Effects of dissociation, pressure and wall temperature gradients, three-dimensional flow, and nose bluntness are included. Simplified methods for making turbulent heating estimates using slide-rules or desk calculators are also presented. The computation of heating rates on a typical reentry configuration in flight and the extrapolation of test data from ground test facilities to flight are described. The turbulent nonsimilar boundary layer approach offers several advantages over previous methods, and is recommended for specific parametric studies of turbulent flows. Calculations made using this method were restricted to ideal gases. Modifications can be made to include real-gas effects.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1967
- Accession Number
- AD0667798
Entities
People
- Carl L. Jaeck
- Richard T. Savage
Organizations
- Boeing