Numerical Simulation Research on the Transonic Aeroelasticity of a High-Aspect-Ratio Wing

Guo, Hao; Li, Guoshuai; Chen, Dehua; Lu, Bo

doi:10.18280/ijht.330422

Cited by 7 publications

(5 citation statements)

References 11 publications

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“…Kilian et al [13] studied the impacts of Reynold number on the flow field in a GT model combustor under atmospheric pressure conditions and found that the frequency of the PVC increases linearly with an increase in the inlet Reynold number of premixed air and methane in non-reacting flow. Similar research conclusions of inlet Reynold number or volumetric flow rate on instability frequency in non-reacting flow also can be found in some other related studies [14]. Furthermore, the occurrence of pressure is relatively more complex in the reacting flow [2].…”

Section: Introductionsupporting

confidence: 85%

Large Eddy Simulation of the PVC Behavior in both Non-Reacting and Reacting Flows with Different Reynold Numbers

Shi¹,

Fu²,

Shen³

et al. 2016

IJHT

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The effects of the Reynold number on the precessing vortex core (PVC) behavior in both non-reacting and reacting flows are numerically studied using a three-dimensional fully compressible large eddy simulation method. The predicted results show that a central toroidal recirculation zone (CTRZ) is generated in the vicinity of the axis of the combustor which is dominated by many small-scale vortices. Meanwhile, two smaller external recirculation zones (ERZs) are established in the vicinity of the sidewall of the combustion chamber. Under combustion conditions, the flow field tends to become complex, and the structure of CTRZ is more irregular compared to that of the non-reacting flow. An increase in the inlet Reynold number enlarges the magnitude of CTRZ and thus produces a more regular and stronger structure of the PVC inside the combustion chamber. Consequently, the breakdown positon of the PVC moves downstream under higher Reynold numbers. The structure of PVCs in the reacting flow mostly located in the regions of the unburned reactants within the per-chamber which is relatively smaller and irregular compared to that in the non-reacting flow. There is a linear increase in pressure oscillations amplitude and frequency with an increase in the inlet Reynold numbers. However, the Strouhal number remains relatively constant in both non-reacting and reacting flows. There is also an anticipated decrease in pressure oscillations and frequency in the reacting flow due to the compressibility effect in the reacting flow.

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Section: Introductionsupporting

confidence: 85%

Large Eddy Simulation of the PVC Behavior in both Non-Reacting and Reacting Flows with Different Reynold Numbers

Shi¹,

Fu²,

Shen³

et al. 2016

IJHT

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“…The Spalart-Allmaras turbulence model was chosen. The mesh deformation is calculated by using RBF combined with the TFI method [29,30]. The wing surface pressure distribution is solved by the N-S equation, and the structural dynamics equation is obtained:…”

Section: Cfd and Fluid-solid Coupling Calculation Methodsmentioning

confidence: 99%

Verification of a Body Freedom Flutter Numerical Simulation Method Based on Main Influence Parameters

et al. 2021

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The body freedom flutter characteristics of an airfoil and a fly wing aircraft model were calculated based on a CFD method for the Navier–Stokes equations. Firstly, a rigid elastic coupling dynamic model of a two-dimensional airfoil with a free–free boundary condition was derived in an inertial frame and decoupled by rigid body mode and elastic mode. In the fluid–solid coupling method, the rigid body was trimmed by subtracting the generalized steady aerodynamic force from the structural dynamic equation. The flutter characteristics were predicted by the variable stiffness method at a fixed Mach number and flight altitude. Finally, validation of the predicted body freedom flutter characteristics was performed through a comparison of theoretical solutions based on a Theodorsen unsteady aerodynamic model for airfoil and experimental results for a fly wing aircraft model. The mechanism of the influence of the bending mode stiffness and the position of the center of gravity on the body freedom flutter characteristics were briefly analyzed.

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“…e RBF can be regarded as a three-dimensional extension of the surface spline interpolation method [29]. Its interpolation formula is expressed as…”

Section: Generation Methods For Dynamic Meshmentioning

confidence: 99%

Transonic Static Aeroelastic Numerical Analysis of Flexible Complex Configuration Wing

Zhang

Guo

et al. 2021

Shock and Vibration

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Diamond back wing is subjected to large deformation while gliding, which significantly changes characteristics of the lift as well as the static stability. For this reason, conventional rigid aircraft assumption cannot meet the requirements of the aerodynamic analysis of such aircrafts for accuracy. In this paper, based on CFD/CSD methods, the static aeroelasticity of a small diameter bomb with diamond back wing was studied. The results showed that static aeroelastic effects cause the slope of lift line to drop by 21% and the aerodynamic centre to move backwards by a 1.5% bomb body length, which will deviate the actual flight performance from the design point, thereby decreasing the cruise efficiency and the cruise range.

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Numerical Simulation Research on the Transonic Aeroelasticity of a High-Aspect-Ratio Wing

Cited by 7 publications

References 11 publications

Large Eddy Simulation of the PVC Behavior in both Non-Reacting and Reacting Flows with Different Reynold Numbers

Large Eddy Simulation of the PVC Behavior in both Non-Reacting and Reacting Flows with Different Reynold Numbers

Verification of a Body Freedom Flutter Numerical Simulation Method Based on Main Influence Parameters

Transonic Static Aeroelastic Numerical Analysis of Flexible Complex Configuration Wing

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