Static and Dynamic SACCON PIV Tests, Part I: Forward Flowfield

Gilliot, Anne; Morgand, Stephane; Monnier, Jean-Claude; Roy, Jean-François Le; Geiler, Claude; Pruvost, Jacques

doi:10.2514/6.2010-4395

Cited by 30 publications

(16 citation statements)

References 7 publications

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“…7. An overview about the static tests results is given by Loeser et al [ 16], a summary about the dynamic wind-tunnel tests is given by Vicroy and Loeser [17], and the PIV data results are presented in two publications by Gilliot [18] and Konrath et al [19].…”

Section: Experimental Approachmentioning

confidence: 98%

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Schütte

Hummel

Hitzel³

2012

Journal of Aircraft

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Within the NATO Research and Technology Organisation Applied Vehicle Technology (AVT)-161 task group, titled "Assessment of Stability and Control Predictions for NATO Air and Sea Vehicles," a 53° swept and twisted lambda wing with rounded leading edges is considered. In a first step, the symmetric flow conditions are analyzed in this paper in order to understand the corresponding flow physics. Experiments by the task group are used to develop proper numerical simulation tools for further applications in the design process of unmanned combat aerial vehicles as a part of future air-combat systems. The philosophy of the configuration under consideration is explained. The vortical flowfield is simulated using the DLR, German Aerospace Center TAU-Code applied with different turbulence models on various computational grids. Finally, a best practice is evaluated for medium and large angles of attack. A combination of these numerical results and experimental data lead to a proper understanding of the complex flow structure. Furthermore, this paper addresses the necessity for the predictability and understanding of controlled and uncontrolled flow separation, together with the interaction of the corresponding vortex systems in order to estimate stability and control issues for the entire flight envelope. NomenclatureA = attachment line C¿ = lift coefficient; ¿/(^oo • S) Cl = rolling moment coefficient; l/(q^ • S • c^f) Clß = rolling moment due to sideslip; 9C,/9Ĉ " = pitching moment coefficient (noseup positive); c" = yawing moment coefficient; «/(í/^, • 5-Cref) c"ß = yawing moment due to sideslip; 9C"/9Ĉ p = pressure coefficient; {p -/'oo)/9oo Cf = root chord length of the model cVef = reference length / = frequency /j = moment of inertia around x I y = moment of inertia around y k = reduced frequency; 27r • / • c,^f/VM = Mach number 9tx) = dynamic pressure coefficient; p^ • V^/2 R = Reynolds number; V^ • c^f/v S = reference area 5 = separation line s = half-span Presented a.s

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Section: Experimental Approachmentioning

confidence: 98%

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Schütte

Hummel

Hitzel³

2012

Journal of Aircraft

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“…A summary of its aerodynamic characteristics is presented in [2]. Experimentalists within the AVT-161 team have conducted both static wind-tunnel tests and dynamic tests on the SACCON configuration undergoing pitch, roll, and yaw oscillation to measure the dynamic stability and aerodynamic characteristics [3][4][5][6]. 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.…”

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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“…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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Static and Dynamic SACCON PIV Tests, Part I: Forward Flowfield

Cited by 30 publications

References 7 publications

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

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

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

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