Computed In-Flight Temperature Response of a 120-mm XM797 Gas Generator TrainingRound Nose Cap

摘要

A computational study is presented of the aerothermal response of an XM797 gasgenerator 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.