Analysis of Supersonic-Hypersonic Flutter of Lifting Surfaces at Angle of Attack

Yates, E. C.; Bennett, Robert M.

doi:10.2514/3.59019

Cited by 17 publications

(7 citation statements)

References 5 publications

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“…Yates [22] similarly used the steady flow conditions from shock-expansion theory in LPT. Yates offered a formulation for the downwash on a rectangular diamond wing in pitch-plunge motion.…”

Section: Developments In Piston Theorymentioning

confidence: 99%

Generalized Formulation and Review of Piston Theory for Airfoils

Meijer

Dala

2016

AIAA Journal

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The present work presents a brief review of some of the notable contributions to piston theory and of its theoretical basis. A generalized formulation of piston theory is given, applicable to both local and classical piston theory. A consistent generalized formulation of the downwash equation is given, accounting for arbitrary motion in the plane of the airfoil. The formulation reduces to established downwash equations through appropriate definition of the cylinder orientation. The theoretical range of validity of Lighthill's classical piston theory is examined, and the relative accuracy of a number of approximate theories encapsulated by the formulation as applied to a planar wedge is considered. The relative importance of higher-order terms in piston theory is examined, with the significance of recent literature extending the fidelity of the firstorder term highlighted. It is subsequently suggested that current implementations of local piston theory may be improved through the use of a first-order term of suitable accuracy.

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“…Yates [22] similarly used the steady flow conditions from shock-expansion theory in LPT. Yates offered a formulation for the downwash on a rectangular diamond wing in pitch-plunge motion.…”

Section: Developments In Piston Theorymentioning

confidence: 99%

Generalized Formulation and Review of Piston Theory for Airfoils

Meijer

Dala

2016

AIAA Journal

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“…Traditional flutter analysis methods typically address aeroelastic stability at zero and low angles of attack (AOAs). However, such ranges of AOAs are not adequately representative of supersonic vehicles [2]. Given the maneuver and overload demands of aircraft, coupled with the limited efficiency of supersonic control surfaces, fin operation at high AOAs has become inevitable, which leads to the challenge of addressing supersonic fin flutter at high AOAs.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Flutter Analysis Using Local Piston Theory with Viscous Correction

Liu,

Xie,

Meng

et al. 2023

Aerospace

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Due to the maneuver and overload requirements of aircraft, it is inevitable that supersonic fins experience high angles of attack (AOAs) and viscous effects at high altitudes. The local piston theory with viscous correction (VLPT) is introduced and modified to account for the 3-dimensional effect. With the contribution of the explicit aerodynamic force expression and enhanced surface spline interpolation, a tightly coupled state-space equation of the aeroelastic system is derived, and a flutter analysis scheme of relatively small computational complexity and high precision is established with a mode tracking algorithm. A wind tunnel test conducted on a supersonic fin confirms the validity of our approach. Notably, the VLPT predicts a more accurate flutter boundary than the local piston theory (LPT), particularly regarding the decreasing trend in flutter speed as AOA increases. This is attributed to the VLPT’s ability to provide a richer and more detailed steady flow field. Specifically, as the AOA increases, the spanwise flow evolves into a gradually pronounced spanwise vortex, yielding an additional downwash and energizing the boundary layer, which is not captured by LPT. This indicates that the precision of LPT/VLPT significantly depends on the accuracy of steady flow results.

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“…(2007, 2008), the first-order and the third-order approximation piston theory are utilized to calculate the unsteady aerodynamics of a two-dimensional airfoil with concentrated nonlinearities. In addition, some other methods, such as local piston theory (Morgan et al., 1958; Chen and Cao, 1990), unsteady shock-expansion theory (Zartarian et al., 1961), unsteady Newtonian impact theory (Yates and Bennett, 1972; McNamara and Friedmann, 2007) have also been employed to analyze airfoils aeroelastics in hypersonic flow. These research results (Morgan et al., 1958; Chen and Cao, 1990; Abbas et al., 2007, 2008; Yang et al., 2010; Wang et al., 2015; Lee and Singh, 2018) have laid important research foundations for the design of an active control system of airfoil flutter.…”

Section: Introductionmentioning

confidence: 99%

Dynamic damage analysis of airfoil flutter for a generic hypersonic flight vehicle

Zhang

Wang

Feng

et al. 2019

Journal of Vibration and Control

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The main aim of this paper is to establish the relationship between the airfoil flutter with the flight dynamics of a generic hypersonic flight vehicle (HFV) and analyze the airfoil damage variation during the airfoil flutter. Based on the motion equations of the two degrees of freedom airfoil model and the longitudinal dynamics of the HFV, an airfoil dynamic model is established. By using a coupling equation, the relationship between airfoil flutter and the flight dynamics is estimated. According to the stress–strain ([Formula: see text]) model and the strain–fatigue damage ([Formula: see text]) model, the influence of the stress on the airfoil flutter damage is analyzed. The simulation results show that the flutter of the airfoil is closely related to the flight dynamics for the HFV and the airfoil flutter damage is closely related to the flutter amplitude of the airfoil.

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Analysis of Supersonic-Hypersonic Flutter of Lifting Surfaces at Angle of Attack

Cited by 17 publications

References 5 publications

Generalized Formulation and Review of Piston Theory for Airfoils

Generalized Formulation and Review of Piston Theory for Airfoils

Experimental and Numerical Flutter Analysis Using Local Piston Theory with Viscous Correction

Dynamic damage analysis of airfoil flutter for a generic hypersonic flight vehicle

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