Computation of Hypersonic Nosetip Heat Transfer Rates for an M829-Like Projectile
Abstract
Computational predictions are presented of in-flight blunt nosetip heat transfer rates or an M829-1 ke projectile configuration. Predictions are made for higher-than-conventional flight velocities up to 3 km/sec (Mach 8.8), for both laminar and turbulent flows. Comparisons are made between two predictive approaches: (1) a time-dependent Navier-Stokes numerical technique and (2) a boundary-layer engineering analysis technique (known as ASCC). Additional comparison is made with wind-tunnel heat transfer measurements for a hemisphere-cylinder configuration at Mach 6.82. The Navier-Stokes predictions agree with the experimental data to within the estimated measurement accuracy. The comparisons between the two predictive approaches show agreement within 10% for laminar flow. For turbulent flow, the two codes agree within 10% at the stagnation point, and within about 30-40% further downstream. The heat transfer rates presented here provide a boundary condition model for subsequent analysis of projectile transient thermal response.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1993
- Accession Number
- ADA263226
Entities
People
- Bernard J. Guidos
- Walter B. Sturek
Organizations
- United States Army Research Laboratory