Transonic aeroelasticity analysis using state-space unsteady aerodynamic modeling

Crouse, Gilbert L.; Leishman, J. Gordon

doi:10.2514/3.46139

Cited by 18 publications

(7 citation statements)

References 14 publications

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“…This section describes our interpretation of the state-space form of the LB model as described by Leishman and Nguyen (1988), Leishman and Crouse (1989) and Crouse and Leishman (1992). The main advantage of using the statespace form is that it can be appended to the structural model to construct a system of ordinary differential equations representing the dynamical system.…”

Section: Lb Dynamic Stall Modelmentioning

confidence: 99%

An assessment of some effects of the nonsmoothness of the Leishman–Beddoes dynamic stall model on the nonlinear dynamics of a typical aerofoil section

Galvanetto

Peiró

Chantharasenawong

2008

Journal of Fluids and Structures

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Section: Lb Dynamic Stall Modelmentioning

confidence: 99%

An assessment of some effects of the nonsmoothness of the Leishman–Beddoes dynamic stall model on the nonlinear dynamics of a typical aerofoil section

Galvanetto

Peiró

Chantharasenawong

2008

Journal of Fluids and Structures

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“…12, the methodology based on indicial functions can be used for an extended range of reduced frequencies and also for large-amplitude maneuvers. The present Note can provide some insight toward developing alternative procedures to determine unsteady loads using CFD and/or to extend the aerodynamic indicial function concept to three-dimensional wings and helicopter blades.…”

Section: Transonic Unsteady Aerodynamic Loadsmentioning

confidence: 99%

Generalized Transonic Unsteady Aerodynamics via Computational-Fluid-Dynamics/ Indicial Approach.

et al. 2005

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Nomenclature b= half-chord length, m C L , C M = lift and moment coefficients in concentrated form; Eq.(1) C Lα , C Mα ; C Lq , C Mq = lift and moment coefficients caused by a change in the angle of attack and in the pitch rate, respectively; Eq. (6) C lα = lift-curve slope, 1/rad h, α = plunging displacement (m) and the twist angle (rad) about the pitch axis, respectively L , M = unsteady lift per unit length, N/m, and moment per unit length, N, respectively q = pitch rate about the reference axis (≡ 2bα/U ∞ = 2α ) t, τ = time variable (s) and its dimensionless counterpart (≡ U ∞ t/b), respectively U ∞ = freestream speed, m/s ρ ∞ = air density, kg/(m s 2 ) ς = parameter denoting dependence on prior motion history φ L , φ M = aerodynamic indicial lift and moment functions in concentrated form; Eqs. (2) and (3) φ α , φ Mα ; φ q , φ Mq = indicial functions in concentrated form; Eq. (6) ω, k = circular and reduced frequencies (≡ ωb/U ∞ )

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“…From these results, one can conclude that the indicial function approach is an accurate one at all frequencies and Mach numbers. On the other hand, as assessed by Crouse and Leishman [27] the methodology based on indicial functions can be used for an extended range of reduced frequencies, and as presented in Nelson and Pelletier [28], also for large amplitude manoeuvres.…”

Section: Supersonic and Hypersonic Flight Speed Regimesmentioning

confidence: 99%

Development of an indicial function approach for the two-dimensional incompressible/compressible aerodynamic load modelling

Marzocca

Librescu

Kim

et al. 2007

Proceedings of the Institution of Mechanical Engineers, Part G:

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By using a combined analytical-computational methodology, a unified modelling of aerodynamic indicial functions covering the incompressible, subsonic compressible, transonic, and supersonic flight speed regimes is presented. The procedure is carried out in conjunction with a computational fluid dynamic analysis. For a plunging-pitching airfoil, selected unsteady aerodynamic load expressions have been supplied, and appropriate procedures enabling one to obtain these loads via the indicial function approach have been presented. While a single indicial function is needed to describe the aerodynamic loads in the incompressible flight speed regime, for cases where the compressibility effects play a dominant role, four indicial functions are needed. Having in view the usefulness of indicial functions towards determination of unsteady aerodynamics loads in both time and frequency domains, and implicitly for aeroelastic response and flutter predictions, the advantages of their implementation and use appear evident. Comparisons and validations of the aerodynamic model against numerical, analytical, and experimental results are presented, and pertinent conclusions are drawn.Keywords: linear/non-linear indicial aerodynamic functions, incompressible and compressible flight speed regimes, two-degrees-of-freedom airfoil aerodynamics JAERO88

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Transonic aeroelasticity analysis using state-space unsteady aerodynamic modeling

Cited by 18 publications

References 14 publications

An assessment of some effects of the nonsmoothness of the Leishman–Beddoes dynamic stall model on the nonlinear dynamics of a typical aerofoil section

An assessment of some effects of the nonsmoothness of the Leishman–Beddoes dynamic stall model on the nonlinear dynamics of a typical aerofoil section

Generalized Transonic Unsteady Aerodynamics via Computational-Fluid-Dynamics/ Indicial Approach.

Development of an indicial function approach for the two-dimensional incompressible/compressible aerodynamic load modelling

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