Accession Number:

ADA263226

Title:

Computation of Hypersonic Nosetip Heat Transfer Rates for an M829-Like Projectile

Descriptive Note:

Final rept. Jan-Dec 1992

Corporate Author:

ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD

Report Date:

1993-04-01

Pagination or Media Count:

32.0

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 kmsec 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.

Subject Categories:

  • Ammunition and Explosives
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE