Afterburning Missile Base Flow Modeling and Analyses

Period of Performance: 09/19/2016 - 09/18/2017

$1000K

Phase 2 SBIR

Recipient Firm

Combustion Research & Flow Technology
6210 Keller's Church Road Array
Pipersville, PA 18947
Firm POC
Principal Investigator

Abstract

A validated, advanced, detailed physics-based CFD capability to accurately model the separated flow physics immediately downstream in the base region of a propulsive supersonic/hypersonic missile with particle loading effects is developed. The high levels of turbulence in the plume have a primary effect on the structure of the base flow and gas/particle drag interaction further complicates base flow modeling, creating a significant challenge in simulation of solid propellant missile base flows. In the Phase II effort, UMiss/NCPA will conduct hot-rocket model tests with various particle loadings/sizes in a turbulent rocket exhaust and collect base region and plume data and imagery at supersonic flight conditions. CRAFT Tech will utilize the experimental data to validate and refine, as necessary, the CFD discrete-phase particle transport models to accurately capture the gas/particle/turbulence interaction effects and their influence on the missile base flow. This work will provide an unprecedented CFD capability to accurately model high-speed particle-laden missile base flows with direct relevance to solid propellant missiles.