Review of Nonlinear Panel Flutter at Supersonic and Hypersonic Speeds

Mei, Chuh; Abdel-Motagaly, K.; Chen, R.

doi:10.1115/1.3098919

Cited by 291 publications

(100 citation statements)

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“…These are the harmonic balance technique [48], perturbation method [49], finite element method [28,29,38,39,50], direct numerical integration technique (DNIT) [26,40,47,[51][52][53][54][55][56][57][58], pseudo-arc length continuation method that complements the DNIT [32,59] and recently the Lyapunov first quantity (LFQ) [8,31,60]. Galerkin's method [72] and DNIT will be considered to solve the integro-differential equation (Eq.…”

Section: Galerkin Methods and Direct Numerical Integration Techniquementioning

confidence: 99%

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A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

et al. 2011

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In this paper, the effect of the system parameters on the flutter of a curved skin panel forced by a supersonic/hypersonic unsteady flow is numerically investigated. The aeroelastic model investigated includes the third-order piston theory aerodynamics for modeling the flow-induced forces and the Von Kármán nonlinear strain-displacement relation in conjunction with the Kirchhoff plate hypothesis for the panel structural modeling. Structural non-linearities are considered and are due to the non-linear coupling between out-of-plane bending and in-plane stretching. The effects of thermal degradation and Kelvin's model of structural damping independent on time and temperature are also considered. The aero-thermo-elastic governing equations are developed from the geometrically imperfect non-linear theory of infinitely long two-dimensional curved panels. Computational analysis and discussion of the finding along with pertinent conclusions are presented.

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Section: Galerkin Methods and Direct Numerical Integration Techniquementioning

confidence: 99%

“…In recent years, there has been renewed interest in supersonic and hypersonic flight vehicles. A thorough review of the non-linear panel flutter was presented by Mei et al [28], whereas a review of the finite element method within a linearized approach of the supersonic panel flutter was given by Bismarck-Nasr [29].…”

Section: Introductionmentioning

confidence: 99%

A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

et al. 2011

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“…The first group consists of studies focusing on panel flutter, which is a localized aeroelastic problem representing a small portion of the skin on the surface of the hypersonic vehicle. [5][6][7][8][9][10] The second group of studies in this area was motivated by a previous hypersonic vehicle, namely the NASP. [11][12][13][14][15][16][17] However, some of these studies dealt with the transonic regime, because it was perceived to be quite important.…”

Section: Nomenclaturementioning

confidence: 99%

“…The curve fit is then calculated by searching for the ζ i and ω i which minimize Eq. (10). At each search step the linear coefficients (a 0 , a i , and b i ) are updated, and the error is recomputed, using the current ζ i and ω i .…”

Section: -50mentioning

confidence: 99%

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

McNamara

Friedmann

Powell

et al. 2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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The aeroelastic and aerothermoelastic behavior of three-dimensional configurations in hypersonic flow regime are studied. The aeroelastic behavior of a low aspect ratio wing, representative of a fin or control surface on a generic hypersonic vehicle, is examined using third order piston theory, Euler and Navier-Stokes aerodynamics. The sensitivity of the aeroelastic behavior generated using Euler and Navier-Stokes aerodynamics to parameters governing temporal accuracy is also examined. Also, a refined aerothermoelastic model, which incorporates the heat transfer between the fluid and structure using CFD generated aerodynamic heating, is used to examine the aerothermoelastic behavior of the low aspect ratio wing in the hypersonic regime. Finally, the hypersonic aeroelastic behavior of a generic hypersonic vehicle with a lifting-body type fuselage and canted fins is studied using piston theory and Euler aerodynamics for the range of 2.5 ≤ M ≤ 28, at altitudes ranging from 10,000 feet to 80,000 feet. This analysis includes a study on optimal mesh selection for use with Euler aerodynamics. In addition to the aeroelastic and aerothermoelastic results presented, three time domain flutter identification techniques are compared, namely the moving block approach, the least squares curve fitting method, and a system identification technique using an Auto-Regressive model of the aeroelastic system. In general, the three methods agree well. The system identification technique, however, provided quick damping and frequency estimations with minimal response record length, and therefore offers significant reductions in computational cost. In the present case, the computational cost was reduced by 75%. The aeroelastic and aerothermoelastic results presented illustrate the applicability of the CFL3D code for the hypersonic flight regime.

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“…The jet-incrossflow interaction is complex, unsteady, and can significantly affect the total control force. The surface pressure distribution is also important when considering sonic fatigue and supersonic panel flutter near fuel injectors in scramjet engines [3].…”

Section: Introductionmentioning

confidence: 99%

Transient interaction between a reaction control jet and a hypersonic crossflow

et al. 2018

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This paper presents a numerical study that focuses on the transient interaction between a reaction control jet and a hypersonic crossflow with a laminar boundary layer. The aim is to better understand the underlying physical mechanisms affecting the resulting surface pressure and control force. Implicit large-eddy simulations were performed with a round, sonic, perfect air jet issuing normal to a Mach 5 crossflow over a flat plate with a laminar boundary layer, at a jet-to-crossflow momentum ratio of 5.3 and a pressure ratio of 251. The pressure distribution induced on the flat plate is unsteady and is influenced by vortex structures that form around the jet. A horseshoe vortex structure forms upstream, and consists of six vortices: two quasi-steady vortices and two co-rotating vortex pairs that periodically coalesce. Shear-layer vortices shed periodically and cause localised high pressure regions that convect downstream with constant velocity. A longitudinal counter-rotating vortex pair is present downstream of the jet, and is formed from a series of trailing vortices which rotate about a common axis. Shear-layer vortex shedding causes periodic deformation of barrel and bow shocks. This changes the location of boundary layer separation which also affects the normal force on the plate. * warrick.miller@adelaide.edu.au.

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Review of Nonlinear Panel Flutter at Supersonic and Hypersonic Speeds

Cited by 291 publications

References 0 publications

A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

Transient interaction between a reaction control jet and a hypersonic crossflow

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