An Interface for Specifying Rigid-Body Motions for CFD Applications

Murman, Scott M.; Chan, William; Aftosmis, Michael J.; Meakin, Robert L.

doi:10.2514/6.2003-1237

Cited by 34 publications

(12 citation statements)

References 5 publications

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“…Some other works to be mentioned include the studies at the University of Maryland [74][75][76]76], the work of Raveh [77,78,20] at the Israel Institute of Technology, the work of Beran [9,79] at the Air Force Research Laboratory, the work of Silva [30,22] at NASA Langley, and the work of Murman [80,81] at NASA Ames. Finally, researchers at the U.S. Air Force Academy (USAFA) have made a strong effort toward the development of unsteady aerodynamic reduced order models applied to flight mechanics and flow control.…”

Section: Current Aerodynamic Modeling Effortsmentioning

confidence: 99%

Reduced order unsteady aerodynamic modeling for stability and control analysis using computational fluid dynamics

Ghoreyshi

Jirasek

Cummings

2014

Progress in Aerospace Sciences

120

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, "Reduced order unsteady aerodynamic modeling for stability and control analysis using computational fluid dynamics" (2014 Contents ABSTRACTRecent advances and challenges in the generation of reduced order aerodynamic models using computational fluid dynamics are presented. The models reviewed are those that can be used for aircraft stability and control analysis and include linear and nonlinear indicial response methods, Volterra theory, radial basis functions, and a surrogate-based recurrence framework. The challenges associated with identification of unknowns for each of the reduced order methods are addressed. A range of test cases, from airfoils to full aircraft, have been used to evaluate and validate the reduced order methods. The motions have different amplitudes and reduced frequencies and could start from different flight conditions including those in the transonic speed range. Overall, these reduced order models help to produce accurate predictions for a wide range of motions, but with the advantage that model predictions require orders of magnitude less time to evaluate once the model is created.Published by Elsevier Ltd.

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Section: Current Aerodynamic Modeling Effortsmentioning

confidence: 99%

Reduced order unsteady aerodynamic modeling for stability and control analysis using computational fluid dynamics

Ghoreyshi

Jirasek

Cummings

2014

Progress in Aerospace Sciences

120

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“…For the planar pitching motion computations, the grid motion was specified through the use of a general interface (28), which was implemented in the distributed version of the Overflow 2 code. This replaced the need for hard coding of the motion that had been required in earlier work using prior generations of the code.…”

Section: Overflow 2 Simulationsmentioning

confidence: 99%

Navier-Stokes Predictions of Dynamic Stability Derivatives: Evaluation of Steady-State Methods

DeSpirito

Silton

Weinacht

2009

Journal of Spacecraft and Rockets

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Approved for public release; distribution is unlimited.ii REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188Public 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, and completing and reviewing the collection 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 Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)September 2008 ARL-TR-4605 SPONSOR/MONITOR'S ACRONYM(S) 9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThe prediction of the dynamic stability derivatives-roll-damping, Magnus, and pitch-damping moments-were evaluated for three spin-stabilized projectiles using steady-state computational fluid dynamic (CFD) calculations. Roll-damping CFD predictions were found to be very good across the Mach number range investigated. Magnus moment predictions were very good in the supersonic flight regime; however, the accuracy varied in the subsonic and transonic flight regime. The best Magnus moment prediction in the subsonic flight regime was for the square-base projectile that did not exhibit highly nonlinear Magnus moments. A primary contribution of this report is the demonstration that the pitch-damping moment can be adequately predicted via steady-state methods rather than resorting to unsteady techniques. The predicted pitch-damping moment compared very well to experimental data for the three projectiles investigated. For one configuration, the pitch-damping moment was predicted by several CFD codes, two different steady-state methods, and a time-accurate planar pitching motion method. All methods compared very well to each other and to the experimental data. iii

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“…The second-order spatial and temporal accuracy options available in the 2.2k version of OVERFLOW are used throughout the present analysis. Dynamic motions are modeled using standard "xml" input files [22].…”

Section: Approachmentioning

confidence: 99%

Dynamic Stability Analysis of Hypersonic Transport During Reentry

Guruswamy

2016

AIAA Journal

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Dynamic stability analysis is performed for a typical future hypersonic transport vehicle during atmospheric flight. Unsteady aerodynamic data in the form of indicial responses are generated by solving the Navier-Stokes equations. Computations needed at multiple Mach numbers and associated angles of attack are computed in a single job by using dual-level parallel script. Validity of the indicial approach is established by comparing results with experiment and the time-integration method. Flutter boundaries associated with pitch and heave rigid-body degrees of freedom are computed. Effect of position of the mass center on flutter boundaries, which is more predominant in the transonic regime, is shown. This work advances stability analysis procedures for next-generation hypersonic vehicles. Nomenclature

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An Interface for Specifying Rigid-Body Motions for CFD Applications

Abstract: An interface for specifying rigid-body motions for CFD applications is presented.

Cited by 34 publications

References 5 publications

Reduced order unsteady aerodynamic modeling for stability and control analysis using computational fluid dynamics

Reduced order unsteady aerodynamic modeling for stability and control analysis using computational fluid dynamics

Navier-Stokes Predictions of Dynamic Stability Derivatives: Evaluation of Steady-State Methods

Dynamic Stability Analysis of Hypersonic Transport During Reentry

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