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Meeting	ACGS Committee Meeting 100 - Cocoa Beach - October 2007
Agenda Location	5 SUBCOMMITTEE D--DYNAMICS, COMPUTATIONS AND ANALYSIS 5.3 CFD Modeling for Aircraft Stability and Control
Title	CFD Modeling for Aircraft Stability and Control
Presenter	Lt. Col. Scott Morton
Affiliation	Eglin AFB
Available Downloads*	presentation
	Downloads are available to members who are logged in and either Active* or attended this meeting.
Abstract	As the capabilities of Computational Fluid Dynamics (CFD) codes to model full aircraft configurations improve, and the speed of massively-parallel machines increase, it is expected that CFD simulations will be used more and more to steer, or in some cases even replace, traditional flight test analyses. The mission of the U.S. Air Force SEEK EAGLE office is to clear any new weapon configuration and loadings for operational use. As more complex weapons are developed and highly asymmetric loadings are requested, the SEEK EAGLE office is tasked with providing operational clearances for literally thousands of different flight configurations. High-fidelity CFD simulations employing the turbulent Navier-Stokes equations are in a prime position to help reduce some of the required wind tunnel and/or flight test workload. However, these types of CFD simulations are still too time-consuming to populate a full stability and control parameter database in a brute-force manner. This presentation outlines and demonstrates a methodology to generate efficient but nonlinear reduced-order aerodynamic loads models from dynamic CFD solutions which in-turn may be used to quickly analyze stability and control characteristics at a particular flight condition. This technique gives stability and control engineers the ability to generate high-fidelity aerodynamic loads models of full aircraft configurations to include complex weapons loadings in a relatively short amount of time. This method may also be used to determine required control surfaces in the corners of the envelope and the overall approach may be used as early as the conceptual design phase. Results based on the US Air Force F-16C fighter aircraft which exemplify the process are discussed as well as the current status and direction of this ongoing research.