Accession Number : ADA302378

Title :   Computed In-Flight Temperature Response of a 120-mm XM797 Gas Generator Training Round Nose Cap.

Descriptive Note : Final rept. Aug-Dec 94,

Corporate Author : ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD

Personal Author(s) : Guidos, Bernard J.

PDF Url : ADA302378

Report Date : OCT 1995

Pagination or Media Count : 45

Abstract : A computational study is presented of the aerothermal response of an XM797 gas generator nosecap. The XM797 nosecap is a critical component in the design of a 1 2O-mm finned kinetic energy (KE) training round projectile. A propellant-filled chamber within the nosecap is designed so that aerodynamic heating ignites the propellant down range, initiating projectile breakup. The objective of this study is to provide the nosecap temperature response, which is necessary to design the chamber geometry. A model for the aerodynamic heat transfer is constructed using a numerical boundary-layer technique. The heat transfer model provides the necessary boundary conditions for a numerical heat conduction analysis, which computes the temperature response throughout the nosecap. Analysis is presented for (1) a 105-mm version of the nosecap for which previous results are available and (2) the 12O-mm version of the nosecap currently of interest.

Descriptors :   *TRAINING AMMUNITION, *AERODYNAMIC HEATING, *PROJECTILE COMPONENTS, *NOSE CAPS, THERMAL PROPERTIES, VELOCITY, HEAT TRANSFER, FLIGHT TESTING, TEMPERATURE, NUMERICAL ANALYSIS, BOUNDARY LAYER, COMPUTATIONAL FLUID DYNAMICS, ANGLE OF ATTACK, PROPELLANTS, PROFILES, RESPONSE, CONFIGURATIONS, THERMAL CONDUCTIVITY, INFLIGHT, AERODYNAMIC DRAG, GEOMETRY, MACH NUMBER, NUMERICAL METHODS AND PROCEDURES, SUPERSONIC FLOW, KINETIC ENERGY PROJECTILES, AEROTHERMODYNAMICS, CONDUCTION(HEAT TRANSFER), NOSE TIPS, CHAMBERS, GAS GENERATING SYSTEMS, EXPLOSIVES INITIATORS.

Subject Categories : Ammunition and Explosives
      Thermodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE