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3 edition of Aeroelastic, CFD, and dynamic computation and optimization for buffet and flutter application found in the catalog.

Aeroelastic, CFD, and dynamic computation and optimization for buffet and flutter application

Aeroelastic, CFD, and dynamic computation and optimization for buffet and flutter application

final report for the period of December 1, 1996-Novemeber 30, 1997 : under research grant NAG-1-648

by

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  • 38 Currently reading

Published by Dept. of Aerospace Engineering, College of Engineering and Technology, Old Dominion University, National Aeronautics and Space Administration, National Technical Information Service, distributor in Norfolk, Va, [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Aeroelasticity.,
  • Angle of attack.,
  • Vortex breakdown.,
  • Aerospace engineering.,
  • Aerodynamic characteristics.,
  • Aircraft.

  • Edition Notes

    Statementby Osama A. Kandil, principal investigator ; submitted by Old Dominion University Research Foundation.
    Series[NASA contractor report] -- 206678., NASA contractor report -- NASA CR-206678.
    ContributionsOld Dominion University. Research Foundation., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15547926M

    Thanks to the increasing slenderness and lightness allowed by new construction techniques and materials, the effects of wind on structures became in the last decades a research field of great importance in Civil Engineering. Thanks to the advances in computers power, the numerical simulation of wind tunnel tests has became a valid complementary activity and an attractive . applied their discrete adjoint methodology with dynamic overset meshes to a large-scale complex helicopter configu-ration. Most recently, Economon et al.8,9 developed a continuous adjoint framework for unsteady aerodynamic and aeroacoustic by: A Spline-Based Modeling Algorithm for Application to Aerodynamic Shape Optimization Based on CFD Analysis In early phases of conceptual design stages for developing a new car in the modern automobile industry, the lack of systematic methodology to efficiently converge to an agreement between the aesthetics and aerodynamic Author: Kisun Song, Kyung Hak Choo, Dimitri Mavris.


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Aeroelastic, CFD, and dynamic computation and optimization for buffet and flutter application Download PDF EPUB FB2

Get this from a library. Aeroelastic, CFD, and dynamic computation and optimization for buffet and flutter application: final report for the period of December 1, Novem under research grant NAG [Osama A Kandil; Old Dominion University.

Research Foundation.; United States. National Aeronautics and Space Administration.]. Firstly, aeroelastic optimization study varying input parameters such as taper ratio, sweep angle, spanwise elasticity and shear modulus is performed to and dynamic computation and optimization for buffet and flutter application book flutter boundary of.

Linearized Aeroelastic Computations in the Frequency Aeroelastic Based on Computational Fluid Dynamics David Amsallem1, Daniel Neumann2, Youngsoo Choi3, Charbel Farhat4 Stanford University, Stanford, CAUSA An iterative, CFD-based approach for aeroelastic computations in the frequency domain is presented.

A comprehensive aeroelastic model developed toward investigating the static divergence, flutter, and dynamic aeroelastic response of composite aerovehicle wings. The procedure for the new flutter speed computation using CFD-based aeroelastic analysis combined with the Aeroelastic identification technique is summarized as shown in Fig.

This process starts with the FE model and computations of natural frequencies and mode shapes. The CFD-based aeroelastic analysis with an arbitrary Mach number and dynamic.

Abstract. The CFD/CSD coupling method is turning into the main research direction for the static/dynamic aeroelastic analyses.

If one wants to use the method for the complex engineering aeroelastic problems, he needs to investigate the relative aeroelastic algorithms, such CFD the numerical computational method of unsteady aerodynamic forces, equivalent low Cited by: 8.

Economical Unsteady High-Fidelity Aerodynamics for Structural Optimization with a Flutter Constraint Robert E. Bartels1 and Bret K. Stanford2 NASA Langley Research Center, Hampton, VA, Structural optimization with a flutter constraint for a vehicle designed to fly in the transonic regime is a particularly difficult task.

Structural Optimization Sandwich Panel Merit Function Flutter Speed Torsional Frequency These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm by: The paper discusses current approaches for the use of computational fluid dynamics in aeroelastic and dynamic computation and optimization for buffet and flutter application book and structural design optimization applications.

Current methods for computational fluid dynamics-based static maneuver load analysis and flutter analysis are reviewed, including related issues such as fluid-structure interface, and moving Cited by: The paper reports aeroelastic CFD studies conducted for a civil and military aircraft configuration.

An aeroelastic method for geometrically complex configurations consisting of multiple components (like flap, slat, pods, weapons etc.) has been developed and deployed to examine aeroelastic behaviour of a high-lift wing. • Our group is responsible for performing an aeroelastic analysis CFD a wing with a drooped leading edge • OpenFOAM is going to be the primary CFD simulation tool for the aeroelastic analysis • C++ based CFD toolbox • Simple Structural Dynamic Model: sixDofRigidBodyMotion solver • CFD compressible solver: rhoCentralFoamFile Size: 4MB.

The Application of Sparse Matrix Techniques to the CFD based Aeroelastic Bifurcation Analysis of a Symmetric Aerofoil k, M.A. Woodgate and ds Department of Aerospace Engineering, University of Glasgow, Glasgow G12 8QQ, U.K. Glasgow University Aerospace Engineering Report Abstract. CFD Calculation of Aerodynamic Indicial Functions for a Generic Fighter Configuration Mehdi Ghoreyshi, Ph.D., Martiqua L.

Post, Ph.D., and Russell M. Aeroelastic, Ph.D. Modeling and Simulation Research Center, U.S. Air Force Academy, Colorado A reduced-order modeling of nonlinear and unsteady aerodynamics based on indicial (step).

Optimization Methods in CFD Fluid Dynamics 3 extended Aeroelastic realistic configurations. This is the underly-ing motivation for the combination of computational fluid dynamics with numerical optimization methods. Some of the earliest studies of such CFD approach were made by Hicks and Henne (Hicks, Murman and Vanderplaats, ; Hicks and.

Aeroelastic simulation of S-duct dynamics using structure-coupled CFD The time-domain coupling of the reduced, modal structural model and the CFD flow solver is achieved using a conventional stag-gered scheme (CSS) [8] exploiting the dual time-stepping algorithm used for time-integration of the flow equations [11].

At each physical. 10th WorldCongress on Structural and MultidisciplinaryOptimization May 19 - 24,Orlando, Florida, USA Static Aeroelastic Stiffness Optimization and Investigation of Forward Swept Composite Wings J.K.S.

Dillinger1, a2, T. Klimmek3, Z. Gu¨rdal4 1 DLR–Institute of Aeroelasticity, Gottingen, Germany, [email protected] 2 Delft University of. In the present study, the CFD-CSD coupled analysis for static and dynamic analysis were performed for the high AR wing of the solar-powered UAV.

FEM model and CFD model of the present high AR wing are established and they are verified. Static and dynamic aeroelastic analyses of the wing using CFD-CSD coupled method are performed. The. Computational Benchmark of Commercial Fluid-Structure Interaction Software for Aeroelastic Applications Nicholas F.

Giannelis1 and Gareth A. Vio of fully coupled Computational Fluid Dynamics (CFD)/Computational Structural Mechanics this discrepancy may be a result of the application of the Baldwin-Lomax turbulence model,File Size: 1MB.

Farhat, "CFD on Moving Grids: From Theory to Realistic Flutter, Maneuvering, and Multidisciplinary Optimization", International Journal of CFD, Vol. 19, pp. () C. Farhat, P. Avery, R. Tezaur and J.

Li, "FETI-DPH: A Dual-Primal Domain Decomposition Method for Acoustic Scattering", Journal of Computational Acoustics, Vol. 13, pp.

The Application of Sparse Matrix Techniques to the CFD based Aeroelastic Bifurcation Analysis of a Symmetric Wing k, M.A. Woodgate, ds and s Department of Aerospace Engineering, University of Glasgow, Glasgow G12 8QQ, U.K.

Abstract. I'm working on an ambitious plan: a procedure for aeroelastic analisys of complete airplane (static aeroelasticity, flutter determination and fully Aeroelastic analisys of a plane -- CFD Online Discussion Forums.

A Computational Fluid Dynamics (CFD) analysis is developed for 3-D rotor unsteady aerodynamic load prediction. It is then coupled to a rotor structural analysis for predicting aeroelastic blade response, airloads and vibration.

The CFD analysis accounts for the elastic deformations using a dynamically deform-ing mesh system. Direct flutter and limit cycle computations of highly flexible wings for efficient analysis and optimization nonlinear beam finite elements and the ONERA dynamic stall tool.

Stiffness and inertial subcritical behavior dilutes the importance of flutter speed as a constraint in the aeroelastic optimization process. Even at flight.

Two time-accurate Computational Fluid Dynamics (CFD) codes were used to compute several flutter points for a typical business jet model. The model consisted of a rigid fuselage with a flexible semispan wing and was tested in the Transonic Dynamics Tunnel at NASA Langley Research Center where experimental flutter data were obtained from M(sub infinity) = to.

Davide Forti and Gianluigi Rozza, Efficient geometrical parametrisation techniques of interfaces for reduced-order modelling: application to fluid–structure interaction coupling problems, International Journal of Computational Fluid Dynamics, /, 28,(), (). For the simulation of control surface buzz accurate prediction of the shock location and the chock strength is essential and this is currently achieved using Euler and RANS based CFD analysis.

To calculate the motion of the control surface only the flap rotation mode needs to be modelled. In the current work the CFD solver is coupled with a modal based FEM solver. CFD-based aeroelastic studies of flapping wings with any kind of prescribed dynamic wing motion are very scarce.

A reasonably detailed literature review on the computational aeroelastic studies of flapping wings has been presented in [10]. Some of the efforts in the area that are not covered in that paper are discussed here.

Kim et al. [7]. a = −1/5, e =−1/10, μ = 20, r 2 = 6/25, and σ = 2/5. Here r is the dimensionless radius of gyration of the wing about the reference point P, σ is the ratio of uncoupled bending to torsional frequencies, μ is the mass ratio parameter reflecting the relative importance of the model mass to the mass of the air affected by the model, and V is the dimensionless freestream.

A Computational Fluid Dynamics (CFD) analysis is developed for 3-D rotor unsteady aerodynamic load prediction. It is then coupled to a rotor structural analysis for predicting aeroelastic blade response, airloads and vibration.

The CFD analysis accounts for the elastic deformations using a dynamically deforming mesh by: Since the development of the dynamic model is a challenging task, as in Ghoreyshi et al.

(), the study presented here employs CFD directly to evaluate aircraft responses at various conditions. The idea behind this paper is to use aircraft’s control surfaces to counteract the gust and to develop a controller for the control surfaces Cited by: 1.

Development of the Adjoint Approach for Aeroelastic Wing Optimization 5 (a) evaluation of the differentiation of the Mesh interpolation tool (term Xa u) for LANN wing (b) evaluation of the differentiation of the pressure interpolation tool (term Rs w) for LANN wing Fig.

1: Evaluation of the derived terms tural residual equation (1). following way. All the aeroelastic simulations are started form the fully converged aerodynamic solution corresponding to the rigid blade. The CFD and CSM codes are then run serially.

At each new time step the propeller is rotated to its new position and several (typically 5) iterations of the CFD code are performed. Static aeroelastic simulation using CFD, comparison with linear method B.B.

Prananta, J.J. Meijer and J. van Muijden This investigation has partly been carried out under a contract awarded by The Netherlands Ministry of Defence monitored by the Royal Netherlands Air Force and as part of NLR’s Basic Research Programme.

A gradient-based optimization technique and a global optimization method were used to seek a maximum flutter speed. Comparison of optimization results from the full-order model (FOM) and PROM shows that the proposed optimization process yields the same optimum flutter speed as the FOM and yet reduces the computation time significantly, by up to.

Abstract: This paper intends to present the application of Computational Fluid Dynamic (CFD) on the design of high subsonic wing of transport aircraft. The computation was performed using RAMPANT, an unstructured, multigrid flow solver.

A 2-D and 3-D model of the wing was created using CATIA (2D and 3D modeling). updated linear aeroelastic analyses are presented as well. The vehicle design, sizing, FEM analyses/parametrics, linear aeroelastic analyses, and CFD loads analyses were performed by Lockheed-Martin [10,11].

Unstructured grids of the N+2 con guration, generated at NASA, are presented along with Euler (inviscid) static aeroelastic and sonic boom. Design of a Low Shear Hydrofoil through the use of Computational Fluid Dynamics and Multi-Objective Design Optimization. Spogis, N.1, Nunhez, J.

1 ESSS, ITC – INTERNATIONAL TRADE CENTER - Rua do Rocio, 10 andar conj/, Vila Olímpia – CEP: – São Paulo– SP – Brazil – Phone: + (55) (11) File Size: KB. Application of High-Fidelity Computational Fluid Dynamics to Design Optimization for Missile Static Stability 11/16/ Dr.

Greg McGowan [email protected], x Co-authors: Dr. James Carpenter V Michael Eidell Dr. Patrick Keistler Dr. Robert Nance. An optimization design method is provided for ducted propeller steady analysis. combines geometry It generation, auto-meshing, optimization algorithm and CFD analysis techniques and make the process automatic operated which helps extend the CFD analysis to the design process.

For test the whole process, a ductedFile Size: KB. A more recent example that combines sophisticated flow solvers and efficient optimization techniques, applied to 2D sails, is described in Ref.

7: the technical strategy is to merge together CFD and numerical optimization, thereby facilitating a much broader utilization of these simulation technologies in vehicle design.

Analysis of Aeroelastic Rotors Using Hybrid CFD Techniques Nonlinear Computational Pdf Lab FUN3D/VorTran-M • Using CFD/CSD for aeroelastic rotor analysis is computationally expensive • Comprehensive Codes are not able to capture the nonlinear aerodynamics associated with many conditions • Hybrid approaches can.Active flutter suppression, which is a part of the group download pdf flight vehicle technologies known as active controls, is an important contributor to the effective solution of aeroelastic instability problems when they pop up late in the development of a new aircraft or, if used from the start of the design process, it is a key element in multidisciplinary design optimization that could lead Cited by: ebook In addition, the ebook of the static stall characteristics of some typical airfoils on the aeroelastic behavior of a flexible wing are investigated.

The results indicate that in a range of static stall angles of attacks there is a specific angle of attack in which the limit cycle oscillation boundary speed has a maximum value.