Numerical Simulation of Maneuvering Combat Aircraft

Schütte, Andreas; Einarsson, Gunnar; Schöning, Britta; Raichle, Axel; Mönnich, W.; Alrutz, Thomas; Neumann, Jens; Heinecke, Jörg

doi:10.1007/3-540-29064-8_14

Cited by 6 publications

(6 citation statements)

References 2 publications

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“…Most of the applications of the Tau-Code in this paper are based on these experiences. Among others, these computational results include work on the VFE-2 [9] configuration, the X-31 [25][26][27], and the F-16 Cranked Arrow Wing Aerodynamics Project International (CAWAPI) [28].…”

Section: A Computational Fluid Dynamics Solver Taumentioning

confidence: 99%

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: A Computational Fluid Dynamics Solver Taumentioning

confidence: 99%

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Schütte

Hummel

Hitzel³

2012

Journal of Aircraft

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“… , any   * u  is a candidate minimizer for (2). From (18), by accounting for (3), the necessary condition (16) is proven □.…”

Section: Energy Consumption Optimizationmentioning

confidence: 98%

“…Feasible approaches to this problem range from purely numerical integration algorithms, whose computational costs are often a constraint to their applicability [2], to model simplifications aimed at achieving analytical closed form solutions, whose parametrization can be further utilized to compute sub-optimal trajectories for cases of increasing intricacy [3] - [5]. Choosing the most suitable integration technique needs a prior careful exploitation of the problem's structure and neglecting this task degrades the performances of the Guidance Navigation and Control subsystems onboard the vehicles [6].…”

Section: Introductionmentioning

confidence: 99%

On the fuel and energy consumption optimization problem in aircraft path planning

L’Afflitto

Sultan

2010

49th IEEE Conference on Decision and Control (CDC)

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“…For transition prediction on airfoils and wings, TAU is coupled to a laminar boundary layer code and an e N -database method [21]. The Chimera technique enhances the flexibility of TAU with respect to independently moving bodies [27]. For the simulation of aeroelasticity phenomena, TAU has been extended to allow geometry and mesh deformation (see [15] and [19]).…”

Section: General Descriptionmentioning

confidence: 99%

MIRACLE – a joint DLR/ONERA effort on harmonization and development of industrial and research aerodynamic computational environment

Cambier

Kroll²

2008

Aerospace Science and Technology

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The main objective of the common DLR/ONERA project MIRACLE is to harmonize the CFD activities and strategies of DLR and ONERA in order to better fulfil the future requirements of transport aircraft industry in Europe. The paper presents the most significant achievements of the co-operative activities, which have been focused on the following objectives: collaborative enhancement and industrialization of the structured and unstructured-hybrid CFD solvers elsA (ONERA) and TAU (DLR); validation of both flow solvers elsA and TAU for industrial applications; identification of an appropriate software architecture for next generation CFD tools.The joint effort of DLR and ONERA on CFD development has accelerated the enhancement of numerical methods for aerodynamic predictions within conventional and unconventional, environmentally friendly aircraft designs. Both, flow solvers elsA and TAU are routinely used in European aircraft industry. The MIRACLE effort is an important step on the road map to meet the future ambitious goals of aircraft research and industry.

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Numerical Simulation of Maneuvering Combat Aircraft

Cited by 6 publications

References 2 publications

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

On the fuel and energy consumption optimization problem in aircraft path planning

MIRACLE – a joint DLR/ONERA effort on harmonization and development of industrial and research aerodynamic computational environment

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