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Opportunity at Air Force Research Laboratory (AFRL)

Computational Algorithm Development for Rocket Propulsion Flowfield Simulations

Location

Aerospace Systems Directorate, RQ/Engineering, Applied Sciences/Computer Sci

RO# Location
13.30.04.B7680 Edwards Air Force Base, CA 93524

Advisers

Name E-mail Phone
Sankaran, Venkateswaran venkateswaran.sankaran@us.af.mil 661.275.5534

Description

Rocket propulsion flowfields offer significant challenges to computational modeling because of the complex turbulent reacting multiphase physics, the presence multiple length and time scales, and the unsteady nature of the flow phenomena. This topic concerns the investigation of numerical algorithmic aspects to address these challenges from the viewpoint of ensuring solution accuracy, robustness, efficiency and scalability. Specific areas of interest include improved flux schemes that can preserve uniform accuracy at all Mach, Reynolds, and Strouhal numbers; high-order accurate spatial and temporal discretizations; enhanced implicit solution techniques; and automated time-step control for the robust solution of stiff and highly nonlinear problems. The technical approach will involve the use of numerical analysis tools such as von Neumann stability, asymptotic theory, and the method of manufactured solutions as well the development and implementation of the algorithms in candidate computational fluid dynamics codes. Particular emphases will be placed on unsteady flow simulations with DES or LES models for turbulence, generalized equations-of-state for high-pressure super-critical problems, finite-rate chemical kinetics, and stochastic-PDF methods for turbulent combustion. Verification and validation will be targeted towards canonical spray and combustion problems, as well as practical rocket flowfield simulations involving solid motors, liquid rocket engines, cryogenic turbomachinery, and/or electric thrusters.

 

Keywords:
Computational fluid dynamics; Algorithm development; Propulsion flowfields; Liquid rocket engines; Solid rocket motors; Cryogenic turbomachinery;

Eligibility

Citizenship:  Open to U.S. citizens
Level:  Open to Postdoctoral and Senior applicants
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