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


Personal Author(s) : Guidos, Bernard J ; Sturek, Walter B


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a263226.pdf


Report Date : Apr 1993


Pagination or Media Count : 32


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.


Descriptors :   *PROJECTILES , *AERODYNAMIC HEATING , VELOCITY , HEAT TRANSFER , TRANSIENTS , MEASUREMENT , RATES , BOUNDARY LAYER , COMPUTATIONAL FLUID DYNAMICS , ENGINEERING , NAVIER STOKES EQUATIONS , FLUID DYNAMICS , CONVECTION(HEAT TRANSFER) , AGREEMENTS , MACH NUMBER , HEATING , CONFIGURATIONS , RESPONSE , FLIGHT , STAGNATION POINT , SUPERSONIC WIND TUNNELS , BLUNT BODIES , HEMISPHERES , LAMINAR FLOW , TIME , TURBULENT FLOW , ACCURACY , COMPARISON , EXPERIMENTAL DATA , PREDICTIONS , MODELS


Subject Categories : Ammunition and Explosives
      Fluid Mechanics


Distribution Statement : APPROVED FOR PUBLIC RELEASE