Unsteady CFD Calculations of Abrupt Wing Stall Using Detached-Eddy Simulation

Forsythe, James R.; Woodson, Shawn H.

doi:10.2514/6.2003-594

Cited by 33 publications

(17 citation statements)

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“…The primary advantage of DES is that it can be applied at high Reynolds numbers as can Reynolds-averaged techniques, but also resolves geometry-dependent, unsteady threedimensional turbulent motions as in LES. The unstructured finite-volume solver Cobalt 20 has been used in conjunction with DES successfully on a number of complex problems, including a supersonic base flow 21 , delta wing vortex breakdown 22 , a square with rounded corners 23 , the F-15E at high angle of attack 24 , and the F/A-18E with unsteady shock buffet 25 .…”

Section: Aiaa 2003-1103mentioning

confidence: 99%

DES Grid Resolution Issues for Vortical Flows on a Delta Wing and an F-18C

Morton

Steenman

Cummings

et al. 2003

41st Aerospace Sciences Meeting and Exhibit

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An assessment of unstructured grids for use in Detached-Eddy Simulations (DES) of vortical flowfields over two configurations, a 70 degree delta wing and an F-18C are presented. The role of the grid in detached eddy simulations of vortical flowfields, including complex features such as vortex breakdown, is assessed on a delta wing with comparison to wind tunnel data. Adaptive mesh refinement is applied to the delta wing grid to improve the focus region aft of the vortex breakdown where massively separated flow exists and unsteady pressures are generated that could impact the loads on vertical tails of more complex configurations. The adaptively refined mesh is compared to the baseline mesh to determine the advantage of the adaptive mesh refinement approach for vortex breakdown. The focus region grid resolution is then applied to an F-18C in the region of the vortex generat ed from the leading edge extension (LEX). The resulting unsteady tail loads are compared to flight test data from the NASA F-18 HARV database. This paper represents one of the first times adaptive mesh refinement will be applied to a detached eddy simulati on of a flight vehicle configuration.

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Section: Aiaa 2003-1103mentioning

confidence: 99%

DES Grid Resolution Issues for Vortical Flows on a Delta Wing and an F-18C

Morton

Steenman

Cummings

et al. 2003

41st Aerospace Sciences Meeting and Exhibit

Self Cite

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“…These and other applications illustrate the capability of DES to accurately resolve chaotic unsteady features in the separated regions along with a rational treatment of the attached boundary layers. Recent DES predictions of the flow around complex configurations (all using Cobalt) include the massively separated flow around an F-15E at 65 o angle of attack reported by Forsythe et al [2004] (this simulation was the first eddy-resolving simulation of flow around a full aircraft configuration), transonic shock-separated flow over an F/A-18E by Forsythe and Woodson [2003], and vortex breakdown on an F-18C by Morton et al [2003Morton et al [ , 2004.…”

Section: Numeric Simulationmentioning

confidence: 99%

Flow Control

Fagley¹

2013

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“…Recent DES predictions of the flow around complex configurations (all using Cobalt) include the massively separated flow around an F-1i5E at 650 angle of attack reported by Forsythe et a/. (2004) (the first eddy-resolving simulation of flow around a full aircraft configuration), transonic shock-separated flow over an F/A-18E by Forsythe and Woodson (2003), and vortex breakdown on an F-1 8C by Morton et al (2003Morton et al ( , 2004.…”

Section: Overview Of Cobalt Cfd Solvermentioning

confidence: 99%

Computational Methods for Feedback Controllers for Aerodynamics Flow Applications

Siegel¹,

Seidel²,

McLaughlin³

et al. 2007

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, end completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information. including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Executive SummaryThis program succeeded in achieving the goal set in the original proposal solicitation, which is the development of a software toolbox to enable feedback flow controller development. Our toolbox is comprehensive in that it covers all aspects of controller development. Starting with data collection of the unforced and open loop forced flow response, through low dimensional model development, controller design and testing all the way to controller verification against a truth model, all important aspects of controller development are covered. Since all feedback control related software is implemented in Matlab, the controller developer can easily implement any control algorithm conceivable, using one of the most popular state of the art 4 th generation programming languages. At the same time, computationally intensive algorithms were parallelized in order to improve execution speed and allow for processing of even the largest data sets. This was done using the highly efficient open source file format hdf5, in order to allow low level access to the data by the user if needed. Based on feedback from industry representatives at the AFOSR contractors meeting in Long Beach earlier this month, we expect the toolbox to become an indispensable tool for controller development not just for academia, but also for applied problems encountered by the industry. The toolbox developed around the Cobalt flow solver allows for physically correct modeling of any flow control mechanism available today, by using rigid body motion, blowing and suction boundary conditions and body forces. This can be done both open loop, dosed loop and even combinations of multiple controllers and different actuation mechanisms acting on a flow field at once can be investigated. These capabilities set the toolbox apart from any other commercially available toolbox, and also surpass the capabilities of existing research codes. Personnel Supported U.S. Air Force Academy

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Unsteady CFD Calculations of Abrupt Wing Stall Using Detached-Eddy Simulation

Cited by 33 publications

References 0 publications

DES Grid Resolution Issues for Vortical Flows on a Delta Wing and an F-18C

DES Grid Resolution Issues for Vortical Flows on a Delta Wing and an F-18C

Flow Control

Computational Methods for Feedback Controllers for Aerodynamics Flow Applications

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