Aeroelastic Simulations of High Reynolds Number Aero Structural Dynamics Wind Tunnel Model

Ritter, Markus; Neumann, Jens; Krüger, Wolf R.

doi:10.2514/1.j053384

Cited by 10 publications

(2 citation statements)

References 12 publications

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“…This paper presents the results of static and dynamic simulations of the Pazy Wing for a range of dynamic pressures and angles of attack. The aeroelastic solver used couples a vortex lattice method (VLM) with the commercial finite element solver MSC Nastran and was successfully used for comparable aeroelastic simulations of complex wind tunnel models and analyses of highly flexible aircraft in free-flight [1,9,13,14]. A brief description is provided in Section 2.2.2.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear Aeroelastic Simulations and Stability Analysis of the Pazy Wing Aeroelastic Benchmark

Hilger

Ritter

2021

Aerospace

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The Pazy wing aeroelastic benchmark is a highly flexible wind tunnel model investigated in the Large Deflection Working Group as part of the Third Aeroelastic Prediction Workshop. Due to the design of the model, very large elastic deformations in the order of 50% span are generated at highest dynamic pressures and angles of attack in the wind tunnel. This paper presents static coupling simulations and stability analyses for selected onflow velocities and angles of attack. Therefore, an aeroelastic solver developed at the German Aerospace Center (DLR) is used for static coupling simulations, which couples a vortex lattice method with the commercial finite element solver MSC Nastran. For the stability analysis, a linearised aerodynamic model is derived analytically from the unsteady vortex lattice method and integrated with a modal structural model into a monolithic aeroelastic discrete-time state-space model. The aeroelastic stability is then determined by calculating the eigenvalues of the system’s dynamics matrix. It is shown that the stability of the wing in terms of flutter changes significantly with increasing deflection and is heavily influenced by the change in modal properties, i.e., structural eigenvalues and eigenvectors.

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Section: Introductionmentioning

confidence: 99%

Nonlinear Aeroelastic Simulations and Stability Analysis of the Pazy Wing Aeroelastic Benchmark

Hilger

Ritter

2021

Aerospace

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“…In this paper, the aeroelastic study of the HIRENASD wing-body [19,20] is selected to evaluate the accuracy of the aeroelastic simulation of the solver. The configuration and the hybrid mesh (shown in Figure 7) were provided by the AePW Conference sponsors.…”

Section: Verification Case Of Staticaeroelsticitymentioning

confidence: 99%

Study on the Aerothermoelastic Characteristics of a Body Flap Considering the Nozzle–Jet Interference

Hua,

Chen,

Wan

et al. 2023

Aerospace

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A body flap/RCS-integrated configuration is often used to achieve pitch trimming and controlled flight in near space for hypersonic vehicles. Under the high temperature and pressure load induced by the expansion wave at the nozzle exit, the body flap is prone to significant structural deformation, which leads to a change in the resulting moment, even comparable to the control ability, and bring additional challenges to the control system. Based on the CFD/CTD/CSD coupling method, the aerothermoelastic effect on the aerodynamic characteristics and structural deformation of the body flap under jet interaction is systematically studied. Numerical results indicate that the pitching moment coefficients show an increasing trend for all the models, rigid, elastic and thermoelastic, while the increment significantly decreases with the increase in trajectory altitudes. With the increase in deflection angle, the pitching moment coefficients of the three models decrease nonlinearly at high altitude, and the aerothermoelastic effect significantly decreases. At a middle-lower altitudes, the pitching moment coefficient is reversed at a lager deflection angle, and the trailing edge of the body flap presents the deformation characteristics of upward bending, which makes the aerothermoelastic phenomenon degenerate into an aeroelastic problem. From the station along the chord and spanwise direction, the change in displacement increment of the thermoelastic model reflects the competitive relationship between normal stress and thermal stress imposed by jet interaction.

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Aerodynamic Metrologists Guide to Dynamic Force Measurement

Burns

Vlajic

Chijioke

et al. 2022

Journal of Aircraft

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Aeroelastic Simulations of High Reynolds Number Aero Structural Dynamics Wind Tunnel Model

Cited by 10 publications

References 12 publications

Nonlinear Aeroelastic Simulations and Stability Analysis of the Pazy Wing Aeroelastic Benchmark

Nonlinear Aeroelastic Simulations and Stability Analysis of the Pazy Wing Aeroelastic Benchmark

Study on the Aerothermoelastic Characteristics of a Body Flap Considering the Nozzle–Jet Interference

Aerodynamic Metrologists Guide to Dynamic Force Measurement

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