Advanced Computational Model for Rocket Plume Effects on Escape System Aerodynamic Characteristics

Period of Performance: 09/22/1997 - 09/22/1999


Phase 2 SBIR

Recipient Firm

CFD Research Corp.
701 McMillian Way NW Suite D
Huntsville, AL 35806
Principal Investigator

Research Topics


In Phase I of this SBIR program,several state-of-the-art CFD tools were adapted and developed for simulating escape system aerodynamics with rocket propulsion. The selected computational tools are based on teh numerical solution ofthe Navier-Stokes equations with advanced turbulence adn chemistry models. The CFD methodologies were validated against a seriew of 2D and 3D nozzle and plume flowfield data. The comparisons to nozzle thrust and plume shape measurements were excellent. An advanced computational environment for the simulation of escape systems with multiple rockets and controllable propulsion was demonstrated by calculating the flow field for an ejection seat with two rockets firing. In Phase II, further development and validation of the computational tools and methodologies will be completed. A boundary condition module for simulating multiple rocket nozzles with controllable propulsion will be developed based on a nozzle exhaust database. The many-to-one grid interface capability will be further developed for local grid refinement. This capability will ensure an efficient and flexible methodology for resolving the high gradient flowfields associated with the rocket plumes. All of the developed tools will be validated against existing test data for two different escape systems, and used to perform aeerodynamic analysisi on NACES with Pintle Escape Propulsion System. The developed tools will be documented and provided to NAWC with necessary user training and support.