Aeroelastic Analysis of a Typical Section using Euler and Navier-Stokes Mesh-less Method

In the present work a comparative study of phase-lagged boundary condition methods is carried out. The relative merits and advantages of time-shifted and the Fourier decomposition methods are compared. Both methods are implemented in a time marching Euler/Navier-Stokes solver and are applied to a flat plate helical fan with harmonically oscillating blades to perform the study. Results were obtained for subsonic as well as supersonic inflows. Results for subsonic inflow showed good comparisons with published results and between the two methods along with comparable computational costs. For the supersonic inflow, despite the presence of shocks at the periodic boundary results from both the methods compared well, however, Fourier decomposition method was computationally more expensive. For linear flowfield Fourier decomposition method is best suited, especially for work-station environment. The time-shifted method is better suited for CRAY category of computers where fast input-output devices are available.

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Static aeroelastic analysis of fighter aircraft using a three-dimensional Navier-Stokes algorithm

10.2514/6.1990-435 ◽

1990 ◽

Cited By ~ 10

Author(s):

DAVID SCHUSTER ◽

JOSEPH VADYAK ◽

ESSAM ATTA

Keyword(s):

Three Dimensional ◽

Navier Stokes ◽

Fighter Aircraft ◽

Aeroelastic Analysis

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Flutter Analysis of a Transonic Fan

Volume 4: Turbo Expo 2002, Parts A and B ◽

10.1115/gt2002-30319 ◽

2002 ◽

Cited By ~ 5

Author(s):

R. Srivastava ◽

M. A. Bakhle ◽

T. G. Keith ◽

G. L. Stefko

Keyword(s):

Energy Exchange ◽

Stokes Equations ◽

Navier Stokes ◽

Exchange Method ◽

Navier Stokes Equations ◽

Aerodynamic Damping ◽

Aeroelastic Analysis ◽

Flutter Analysis ◽

Blade Shape ◽

Transonic Fan

This paper describes the calculation of flutter stability characteristics for a transonic forward swept fan configuration using a viscous aeroelastic analysis program. Unsteady Navier-Stokes equations are solved on a dynamically deforming, body fitted, grid to obtain the aeroelastic characteristics using the energy exchange method. The non-zero inter-blade phase angle is modeled using phase-lagged boundary conditions. Results obtained show good correlation with measurements. It is found that the location of shock and variation of shock strength strongly influenced stability. Also, outboard stations primarily contributed to stability characteristics. Results demonstrate that changes in blade shape impact the calculated aerodynamic damping, indicating importance of using accurate blade operating shape under centrifugal and steady aerodynamic loading for flutter prediction. It was found that the calculated aerodynamic damping was relatively insensitive to variation in natural frequency.

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Composite material structure optimization design and aeroelastic analysis on forward swept wing

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410018807810 ◽

2018 ◽

Vol 233 (13) ◽

pp. 4679-4695 ◽

Cited By ~ 1

Author(s):

Xue Rongrong ◽

Ye Zhengyin ◽

Ye Kun ◽

Wang Gang

Keyword(s):

Optimization Design ◽

Navier Stokes ◽

Aerodynamic Load ◽

Material Structure ◽

Swept Wing ◽

Aeroelastic Tailoring ◽

Aeroelastic Analysis ◽

Material Orientation ◽

Weight Penalty ◽

Divergence Problem

The static aeroelastic torsion divergence problem is the main obstacle to bring forward swept wing into massive applications. The aeroelastic tailoring technique-based radial basis function neural networks (RBFNNs) and genetic algorithm (GA) optimization in MATLAB considering the material orientation, thickness, and lay-up are elucidated in the present work. RBFNNs are used to build a surrogate model between the composite parameters and structure displacement, which is proved robust and accurate. Then an optimal structure is obtained by GA global search based on RBFNNs model with the weight constrain. The displacements of the forward swept wing caused by an approximate aerodynamic load are decreased 32.5% through finite element method (FEM) static structural analysis. The modal analysis illustrates that the first mode frequency increases by 33.0% and the second mode increases by 37.9%. A computational aeroelasticity approach is developed by in-house Hybrid Unstructured Reynolds-Averaged Navier-Stokes solver associating an open source FEM code – Calculix. The results of coupling calculations show effectiveness of aeroelastic tailoring optimization of composite forward swept wing without weight penalty. The results obtained demonstrate that for the forward swept wing, the most violent situation appears around Mach Number 1.0 where the aeroelastic tailoring optimization could decrease the torsion angle by nearly 70.0%. The torsion of forward swept wing will increase at subsonic and decrease at supersonic with the increase of velocity.

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