Transient, Rocket Exhaust Plume Modeling for Static Test Analyses

Award Information
Agency:
Department of Defense
Branch:
Army
Amount:
$69,991.00
Award Year:
2006
Program:
SBIR
Phase:
Phase I
Contract:
W31P4Q-07-C-0032
Agency Tracking Number:
A062-020-0394
Solicitation Year:
2006
Solicitation Topic Code:
A06-020
Solicitation Number:
2006.2
Small Business Information
COMBUSTION RESEARCH AND FLOW TECHNOLOGY,
6210 Keller's Church Road, Pipersville, PA, 18947
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
929950012
Principal Investigator
 Brian York
 Principal Scientist & Treasurer
 (215) 766-1520
 york@craft-tech.com
Business Contact
 Brian York
Title: Principal Scientist & Treasurer
Phone: (215) 766-1520
Email: york@craft-tech.com
Research Institution
N/A
Abstract
Our proposal addresses the high fidelity modeling of transient rocket exhaust plumes in a static test environment. Static testing provides a practical means of obtaining plume signature and interference data to support model validation. However, existing CFD codes routinely used for plumes in flight cannot accurately address many of the complexities associated with a static test environment. As such, we will extend an advanced state of the art Navier-Stokes code that contains much of the requisite physics (finite-rate chemistry, multiphase particulates, condensation/vaporization, etc.)and can operate in a dynamic grid framework. In Phase I, we will investigate the use of “all-speed” preconditioning techniques for mixed regions of high and low speed flow. We will formulate a technical approach to efficiently model a rocket motor exhausting into a quiescent environment including the effects of the test stand, the surrounding terrain, prevailing wind, and physical phenomena such as buoyancy, and secondary smoke formation. Procedures will be devised to accurately model the transient “start-up” and “shutdown” events of the rocket motor firing. We will demonstrate the ability of the extended model to analyze a transient rocket exhaust plume for a static test condition for a simplified geometrical configuration.

* information listed above is at the time of submission.

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