Computational Study of Static And Dynamic Vortical Flow over the Delta Wing SACCON Configuration Using the FOI Flow Solver Edge

Tormalm, Magnus; Schmidt, Stefan

doi:10.2514/6.2010-4561

Cited by 26 publications

(20 citation statements)

References 4 publications

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“…The prevalent experimental methodology for quantifying the dynamic stability of an aircraft calls for extracting the dynamic stability derivatives from the force and moment (F&M) coefficients as the aircraft undergoes a periodic motion about a body axis in a wind tunnel. Other team members are running parallel dynamic computational studies following a similar approach of modeling SACCON undergoing pitch, roll, and yaw oscillation with their respective CFD tools [7][8][9][10][11][12][13]. The collective experiences from these studies have confirmed the difficulty of achieving accurate and efficient computation of dynamic stability characteristics.…”

Section: Introductionmentioning

confidence: 99%

Three Unstructured Computational Fluid Dynamics Studies on Generic Unmanned Combat Aerial Vehicle

Frink

Tormalm

Schmidt

2012

Journal of Aircraft

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Three independent studies from the United States (NASA), Sweden (Swedish Defense Research Agency), and Australia (Defense Science and Technology Organization) are analyzed to assess the state of current unstructured grid computational fluid dynamic tools and practices for predicting the complex static and dynamic aerodynamic and stability characteristics of a generic 53-deg swept, round-leading-edge uninhabited combat air vehicle configuration, called SACCON (which stands for "stability and control configuration"). NASA exercised the USM3D tetrahedral cell-centered flow solver, while the Swedish Defense Research Agency and the Defense Science and Technology Organization applied the Swedish Defense Research Agency/EDGE general-cell vertex-based solver. The authors primarily employ tbe Reynolds-averaged Navier-Stokes assumption, with a limited assessment of the EDGE detached eddy simulation extension, to explore sensitivities to grids and turbulence models. Correlations with experimental data are provided for force and moments, surface pressure, and off-body flow measurements. The vortical flowfield over SACCON proved extremely difflcult to model adequately. As a general rule, the prospect of obtaining reasonable correlations of SACCON pitching moment characteristics with the Reynolds-averaged Navier-Stokes formulation is not promising, even for static cases. However, dynamic pitch oscillation results seem to produce a promising characterization of shapes for the lift and pitching moment hysteresis curves. Future studies of this configuration should include more investigation with higher-fidelity turbulence models such as detached eddy simulation. b C," or CM f k log(r/rO) MRP Nomenclature wing span, 1.54 m lift coefficient, lift/

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Section: Introductionmentioning

confidence: 99%

Three Unstructured Computational Fluid Dynamics Studies on Generic Unmanned Combat Aerial Vehicle

Frink

Tormalm

Schmidt

2012

Journal of Aircraft

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“…The mesh is constructed with an O topology and thirteen blocks. The geometry of the case is based on the information provided in Schütte et al [53] and Tormalm and Schmidt [26]. We analyze the flow around the UCAV using a RANS flow solver [47] with a Spalart-Allmaras turbulence model [54].…”

Section: Saccon Ucav: Test Case Descriptionmentioning

confidence: 99%

“…The data were then analyzed with the same techniques used to produce stability derivatives from forced-oscillation wind tunnel data, which allowed the method to take advantage of the large body of knowledge in that field. A number of papers from the recent NATO RTO Task Group AVT-161 have explored the use of forced oscillation techniques with a variety of CFD solvers [22], including Reynolds-averaged Navier-Stokes (RANS) [23,24], direct eddy simulation (DES) [25,26], and harmonic balance [27] solvers. The results were shown to correlate well with experimental data.…”

Section: Introductionmentioning

confidence: 99%

Computing Stability Derivatives and Their Gradients for Aerodynamic Shape Optimization

Mader

Martins

2014

AIAA Journal

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“…The third facet is focused on a naval application. The task group is currently in progress, and a first reporting of their results is contained primarily in two special sessions at this 28 th AIAA Applied Aerodynamics Conference [references [77][78][79][80][81][82][83][84][85][86][87][88][89].…”

Section: Avt-161mentioning

confidence: 99%

A Survey of Factors Affecting Blunt-Leading-Edge Separation for Swept and Semi-Slender Wings

Luckring

2010

28th AIAA Applied Aerodynamics Conference

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A survey is presented of factors affecting blunt leading-edge separation for swept and semi-slender wings. This class of separation often results in the onset and progression of separation-induced vortical flow over a slender or semi-slender wing. The term semi-slender is used to distinguish wings with moderate sweeps and aspect ratios from the more traditional highly-swept, low-aspect-ratio slender wing. Emphasis is divided between a selection of results obtained through literature survey a section of results from some recent research projects primarily being coordinated through NATO's Research and Technology Organization (RTO). An aircraft context to these studies is included.

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Computational Study of Static And Dynamic Vortical Flow over the Delta Wing SACCON Configuration Using the FOI Flow Solver Edge

Cited by 26 publications

References 4 publications

Three Unstructured Computational Fluid Dynamics Studies on Generic Unmanned Combat Aerial Vehicle

Three Unstructured Computational Fluid Dynamics Studies on Generic Unmanned Combat Aerial Vehicle

Computing Stability Derivatives and Their Gradients for Aerodynamic Shape Optimization

A Survey of Factors Affecting Blunt-Leading-Edge Separation for Swept and Semi-Slender Wings

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