Correction of unsteady aerodynamic influence coefficients using experimental or CFD data

Brink-Spalink, Jan; Bruns, J. E.

doi:10.2514/6.2000-1489

Cited by 20 publications

(20 citation statements)

References 2 publications

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“…The vortex lattice method (VLM) [18] is a fast panel method suitable for aerodynamic loads simulation in the aeroelastic sizing process. Due to the underlying theory, its validity is limited to the subsonic regime but transonic effects can be considered using various correction techniques [19][20][21][22] or an enhancement with CFD calculations for selected parameters [23].…”

Section: Aerodynamic Modelmentioning

confidence: 99%

Design and sizing of an aeroelastic composite model for a flying wing configuration with maneuver, gust, and landing loads

2020

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The paper addresses the application of a parametric design process for a flying wing configuration. The multi-disciplinary configuration (MULDICON) is a generic unmanned combat air vehicle (UCAV) developed for research purposes, a further development of the DLR-F19 configuration, which was used for research activities in the scope of the DLR project Mephisto and its predecessors FaUSST and UCAV2010. For the MULDICON, the DLR parametric design process MONA is applied. Special emphasis is placed on the structural modeling with composite material where each layer is modeled and analyzed. Various failure criteria are compared to define suitable constraints for the optimization of the load carrying structure. In contrast to optimize the thickness of composites with global allowable strains, such strategy allows for a detailed analysis of every layer. The number of constraints due to the set-up of every ply is substantially increased compared to the strain allowables but the structural optimization is still applicable. The detailed structural and mass models represent the global stiffness and structural dynamic characteristics of the aircraft. For the loads analysis part of the design process, 9 different mass configurations with a total of 306 maneuvering load cases as well as 336 1-cos gust load cases are taken into account. Furthermore, a new simplified landing impact simulation is introduced to consider 12 landing load cases. All load cases are defined according to regulations like CS-25. Such number of load cases is necessary to cover a sufficient number of flight conditions. For the selection of the design loads for the structural optimization, the essential loads are analyzed for a subset of locations. Together with a parametrized optimization model, the structural optimization is conducted. The result is a weight-optimized structural model for the MULDICON. This entire model allows for the investigation of physics-based effects already at an early stage of the design process.

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Section: Aerodynamic Modelmentioning

confidence: 99%

Design and sizing of an aeroelastic composite model for a flying wing configuration with maneuver, gust, and landing loads

2020

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“…Thus, the range of application of this method is limited. Corrections of the DLM results can be made based on data from computational fluid dynamics (CFD) simulations or wind tunnel tests to compensate for these assumptions [2,3]. An advantage of the DLM is its formulation in the frequency domain, which eases unsteady analysis in terms of computing time.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Simulations of High Reynolds Number Aero Structural Dynamics Wind Tunnel Model

2016

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This article presents results of numerical simulations of the High Reynolds Number Aero Structural Dynamics wind tunnel configuration. The activities consist of the selection of relevant transonic test cases, the setup and simulation of the numerical models, and the comparison of computational and experimental results. Two steady (static coupling) and three unsteady (forced motion) test cases were selected, all in the transonic flow regime at Mach numbers up to 0.85 and Reynolds numbers up to 23 million. Good agreement between numerical and experimental data was obtained for both the steady and the unsteady test cases. It is shown that the consideration of the static elastic deformation of the wing is indispensable for both the steady and unsteady simulations. The unsteady simulations were executed in such a way that the elastic motion of the wing in a selected structural eigenmode was prescribed in a forced motion computational fluid dynamics simulation using grid deformation. This approach yields very satisfactory results in terms of the unsteady pressure distribution.

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“…Due to fluid dynamics similitude [81], the approximate lift-deficiency functions may finally be parametrised with respect to few fundamental nondimensional numbers, such as Reynolds, Mach and Strouhal numbers of the airflow [82] as well as sweep angle, aspect and thickness ratios of the aircraft wing [42]; correction-based approaches have also been proposed in order to retain the high accuracy of nonlinear CFD at the low computational costs of linear potential-flow aerodynamics [83][84][85][86].…”

Section: Introductionmentioning

confidence: 99%

Semi-Analytical Reduced-Order Models for the Unsteady Aerodynamic Loads of Subsonic Wings

Berci¹

2015

Proceedings of the 5th International Conference on Computational Methods in Structural Dynamics and Earthquake Engineering (COM

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Correction of unsteady aerodynamic influence coefficients using experimental or CFD data

Cited by 20 publications

References 2 publications

Design and sizing of an aeroelastic composite model for a flying wing configuration with maneuver, gust, and landing loads

Design and sizing of an aeroelastic composite model for a flying wing configuration with maneuver, gust, and landing loads

Aeroelastic Simulations of High Reynolds Number Aero Structural Dynamics Wind Tunnel Model

Semi-Analytical Reduced-Order Models for the Unsteady Aerodynamic Loads of Subsonic Wings

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