A Compact CFD-Based Reduced Order Modeling for Gust Analysis

Wang, Z.; Zhang, Z.; Sarhaddi, D.

doi:10.2514/6.2011-2041

Cited by 11 publications

(3 citation statements)

References 11 publications

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“…This method has been used for relatively simple to moderately complex configurations, for example Singh and Baeder, 11 Zaide and Raveh, 18 Raveh, 19,20 and Wang et al 21 It was recently used to simulate the aeroelastic response of a launch vehicle to a sequence of one-minus-cosine gusts. 13 In this study a one-minus-cosine and a sharp-edged gust profile will be used.…”

Section: The Field Velocity Methods and Discrete Gust Modelmentioning

confidence: 99%

Developing an Accurate CFD Based Gust Model for the Truss Braced Wing Aircraft

Bartels

2013

31st AIAA Applied Aerodynamics Conference

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Section: The Field Velocity Methods and Discrete Gust Modelmentioning

confidence: 99%

Developing an Accurate CFD Based Gust Model for the Truss Braced Wing Aircraft

Bartels

2013

31st AIAA Applied Aerodynamics Conference

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“…20 It has a 120 ft span and 8 ft chord, and a 10% dihedral of the outboard third-span. The wing is clamped at the root.…”

Section: Gust Responses About a Hale Wing (Rigid)mentioning

confidence: 99%

“…The methodology was demonstrated using a generic transport model excited by oneminus-cosine gust profiles, and was also applied to nonlinear gust load analysis in the transonic domain. 19 Similar gust analysis capability (in which gust velocities are introduced only to the surface) was recently introduced to the commercial code ZEUS, 20 including Proper Orthogonal Decomposition-based reduced order modeling of the sharp edge gust response for computational efficiency. All of the above cited CFDbased gust analyses were based on solutions of the Euler inviscid flow equations.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Gust Response in High Angles of Attack

Raveh

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The paper presents Navier-Stokes turbulent simulations of gust responses of a rigid airfoil and of a rigid wing configuration about high mean angles of attack, close to stall, in Reynolds numbers in the order of one million. Responses show that flow separation associated with high angles of attack significantly affect the lift build-up dynamics. Airfoil sharp-edge gust response about high mean angle of attack does not resemble the Kussner function. It involves an initial sharp rise of the lift, which overshoots the steady state value. The maximum lift force that develop in response to a one-minus-cosine gust about high mean angle of attack can be either higher or lower than the response about zero mean angle of attack, depending on the gust gradient length. For short gusts, a dynamic stall effect is observed, where the maximum lift response is higher than that computed about small mean angles of attack, while for longer gusts the maximum lift response is smaller. For the rigid HALE wing case, the lift that develop in response to a one-minus-cosine gust about high mean angle of attack is lower than the response about low mean angles of attack.Since the gust response about high angles of attack does not scale linearly, convolution with sharp-edge gust response does not serve well for prediction of the gust response, and full simulation is required for accurate estimation of the gust loads.

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A reduced-order-model-based multiple-in multiple-out gust alleviation control law design method in transonic flow

Chen

Xian

2013

Sci. China Technol. Sci.

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A Compact CFD-Based Reduced Order Modeling for Gust Analysis

Cited by 11 publications

References 11 publications

Developing an Accurate CFD Based Gust Model for the Truss Braced Wing Aircraft

Developing an Accurate CFD Based Gust Model for the Truss Braced Wing Aircraft

Aerodynamic Gust Response in High Angles of Attack

A reduced-order-model-based multiple-in multiple-out gust alleviation control law design method in transonic flow

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