Numerical Simulation of Maneuvering Aircraft by Aerodynamic, Flight Mechanics and Structural Mechanics Coupling

Schütte, Andreas; Einarsson, Gunnar; Raichle, Axel; Schöning, Britta; Orlt, Matthias; Neumann, Jens; Arnold, Johannes; Mönnich, W.; Forkert, T.

doi:10.2514/6.2007-1070

Cited by 32 publications

(30 citation statements)

References 1 publication

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“…In Fig. 8 results of a viscous Chimera calculation for a delta wing with trailing edge flaps are shown [43]. The component mesh of the flap is designed to allow a flap deflection of ±15…”

Section: Figmentioning

confidence: 99%

“…Within the DLR internal project SikMa [5,44] a multidisciplinary simulation tool for maneuvering aircraft is being developed and validated. The unstructured, time-accurate flow solver TAU is coupled with a computational module solving the flight-mechanic equations and a structural mechanics code determining the structural deformations.…”

Section: Multidisciplinary Simulationsmentioning

confidence: 99%

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Mathematical Modelling of Flow through Pleated Cartridge Filters

Nassehi

Waghode

Hanspal

et al. 2006

Progress in Industrial Mathematics at ECMI 2004

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Summary. Some years ago the national CFD project MEGAFLOW was initiated in Germany, which combined many of the CFD development activities from DLR, universities and aircraft industry. Its goal was the development and validation of a dependable and efficient numerical tool for the aerodynamic simulation of complete aircraft which met the requirements of industrial implementations. The MEGAFLOW software system includes the block-structured Navier-Stokes code FLOWer and the unstructured Navier-Stokes code TAU. Both codes have reached a high level of maturity and they are intensively used by DLR and the German aerospace industry in the design process of new aircraft. Recently, the follow-on project MEGADESIGN was set up which focuses on the development and enhancement of efficient numerical methods for shape design and optimization. This paper highlights recent improvements and enhancements of the software. Its capability to predict viscous flows around complex industrial applications for transport aircraft design is demonstrated. First results concerning shape optimization are presented.

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“…In Fig. 8 results of a viscous Chimera calculation for a delta wing with trailing edge flaps are shown [43]. The component mesh of the flap is designed to allow a flap deflection of ±15…”

Section: Figmentioning

confidence: 99%

Section: Multidisciplinary Simulationsmentioning

confidence: 99%

Mathematical Modelling of Flow through Pleated Cartridge Filters

Nassehi

Waghode

Hanspal

et al. 2006

Progress in Industrial Mathematics at ECMI 2004

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show abstract

“…It has been a subject of numerous flight tests, [15][16][17][18][19] wind tunnel tests 20,21 and CFD. 22,23 This test case has been provided to the partners participating in NATO RTO task group AVT-161 Assessment of Stability and Control Prediction Methods for NATO Air and Sea Vehicles. The objective of this task group is to evaluate CFD codes against wind tunnel data sets of two different aircraft configurations.…”

Section: X-31 Aircraft Modelmentioning

confidence: 99%

Assessment of Sting Effect on X-31 Aircraft Model Using CFD

Jirasek

Cummings

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The article describes the computational evaluation of the effect a belly mounted sting on the aerodynamics characteristics of an X-31 wind tunnel model. The investigation includes results of steady and time-dependent CFD analysis of the X-31 model with and without sting. The values of the steady lift and pitching moment coefficients as well as the pitching moment of model undergoing a manuever are compared to each other and to the wind tunnel data. The results of this analysis show the detrimental effect of sting on stability of the vortical structure above the wing as well as a substantial increase of noise in pitching moment data.

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“…It has been a subject of numerous flight tests, [29][30][31][32][33] wind tunnel tests 34,35 and CFD. 36,37 This test case has been provided to the partners participating in NATO RTO task group AVT-161 (Assessment of Stability and Control Prediction Methods for NATO Air and Sea Vehicles). The objective of this task group is to evaluate CFD codes against wind tunnel data sets of two different aircraft configurations.…”

Section: X-31 Aircraft Modelmentioning

confidence: 99%

Application of Volterra Functions to X-31 Aircraft Model Motion

Cummings

2009

27th AIAA Applied Aerodynamics Conference

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Recent advances towards an efficient computational method for accurately determining the stability and control characteristics of an aircraft are discussed and critiqued. The present approach with greatest promise is to reduce the number of high-fidelity CFD sim ulations by using Volterra functions Reduced Order Modeling. This type of reduced order model is a predictive model which has a unique training maneuver -a unit impulse. The advantage of such an approach is the fast prediction of the aerodynamic characteristics of an aircraft. This article presents the results of application of the Volterra functions ROM for prediction of linear movement of a 2D airfoil and of an X-31 aircraft model. The Volterra ROM predicted well normal and axial force which are linear or weakly non-linear and was in a fairly good agreement with pitching moment as long as the pitching moment predictions were weakly non-linear.

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Numerical Simulation of Maneuvering Aircraft by Aerodynamic, Flight Mechanics and Structural Mechanics Coupling

Abstract: Red-flap grid Blue-back ground cut out box Blue-rigid Red-elastic

Cited by 32 publications

References 1 publication

Mathematical Modelling of Flow through Pleated Cartridge Filters

Mathematical Modelling of Flow through Pleated Cartridge Filters

Assessment of Sting Effect on X-31 Aircraft Model Using CFD

Application of Volterra Functions to X-31 Aircraft Model Motion

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