Application of the Doublet-Lattice Method to Nonplanar Configurations in Subsonic Flow

Kalman, Terez P.; Rodden, William P.; Giesing, Joseph P.

doi:10.2514/3.59117

Cited by 84 publications

(27 citation statements)

References 8 publications

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“…The doublet-lattice method is a very well-established procedure for the calculation of linear unsteady aerodynamic matrices in subsonic compressible flow [29][30][31][32][33][34][35][36][37][38]. In the present paper, a dedicated doublet-lattice code is developed.…”

Section: Present Doublet-lattice Methodsmentioning

confidence: 99%

“…Computer capabilities such as the doublet-lattice-method (DLM) codes [29][30][31][32][33][34][35][36][37][38], PANAIR [39], ZAERO [40][41][42], and other linear potential aerodynamic codes are used and are still being used successfully in aeroelastic analyses of flight vehicles over a wide range of flight conditions. These codes can be used to model general three-dimensional configurations made of lifting surfaces, control surfaces, fuselages, nacelles, external stores, etc.…”

Section: Introductionmentioning

confidence: 99%

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Dynamic Aeroelasticity of Structurally Nonlinear Configurations Using Linear Modally Reduced Aerodynamic Generalized Forces

Demasi

Livne

2009

AIAA Journal

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Steady-state and time-domain methods are introduced for integrating commonly used frequency-domain unsteady aerodynamic modeling based on a modal approach with full-order finite element models for structures with geometric nonlinearities. The methods are aimed at airplane configurations in which geometric-stiffness effects are important but deformations are moderate, flow is attached, and linear unsteady aerodynamic modeling is adequate, such as joined-wing and strut-braced wings at small-to-moderate angles of attack or a low-aspect-ratio wing. The approach proposed in this paper is to use the full-order structural matrices to capture the nonlinear structural behavior and modally reduced aerodynamic matrices calculated by adopting a frequency-domain-based commercial code such as ZAERO or a doublet-lattice method or linearized modal-based generalized aerodynamic matrices generated by computational fluid dynamics codes.

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Section: Present Doublet-lattice Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Dynamic Aeroelasticity of Structurally Nonlinear Configurations Using Linear Modally Reduced Aerodynamic Generalized Forces

Demasi

Livne

2009

AIAA Journal

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“…We then obtain the numerical form for the induced incidence from Eqs. (7) and (8) We then assume the product variation across the strip (14) i also to have a parabolic b n y…”

Section: Applicationsmentioning

confidence: 99%

Spanwise distribution of induced drag in subsonic flow by the vortexlattice method

Giesing¹,

Kalman²,

Rodden³

1970

Journal of Aircraft

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Nomenclature A = aspect ratio Cot = total induced drag coefficient of surface CDW = total induced drag coefficient given by Vortex Lattice Method CD^ = total induced drag given by wake integral CL = total lift coefficient of surface c = chord length of strip c = average chord length of surface Cdi = induced drag coefficient of strip ci = lift coefficient of strip Dd = normalwash factor at bound vortex DC -normalwash factor at control point d = induced drag coefficient of box e = semiwidth of strip M = Mach number p = pressure coefficient of box S = reference area s = semispan of surface Wb = dimensionless normalwash at bound vortex w c = dimensionless normalwash at control point x,y,z = Cartesian coordinates a.= angle of attack ai = induced incidence at bound vortex 77 = dummy spanwise coordinate

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“…WE wish to take issue with Hua 1 who contends that "In the steady aerodynamic forces area, Woodward, 2 Belotserkovskii, 3 Hedman, 4 and Kalman et al 5 have made their prominent contributions. However, most of their works are only concerning the longitudinal forces and moment.…”

mentioning

confidence: 99%

Comment on "A Finite-Element Method for Calculating Aerodynamic Coefficients of a Subsonic Airplane"

Rodden

Giesing

Kalman

et al. 1974

Journal of Aircraft

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Next, IFB is incorporated into the aircraft dynamics. Various values for Q and R in the PI, Eq. (9), were investigated. The values Q = diam[l, 1, 1, 1. l]; R = diam [lO, 10] were selected on the basis of low proportional differential and integral feedback gain values and such that the eigenvalues of the closed-loop airplane are similar to those of the closed-loop model. The gain values are Typical time history results are shown in Fig. 2. These results illustrate the decoupling and the zero state error properties and the good transient behavior for this formulation of the problem.

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Application of the Doublet-Lattice Method to Nonplanar Configurations in Subsonic Flow

Cited by 84 publications

References 8 publications

Dynamic Aeroelasticity of Structurally Nonlinear Configurations Using Linear Modally Reduced Aerodynamic Generalized Forces

Dynamic Aeroelasticity of Structurally Nonlinear Configurations Using Linear Modally Reduced Aerodynamic Generalized Forces

Spanwise distribution of induced drag in subsonic flow by the vortexlattice method

Comment on "A Finite-Element Method for Calculating Aerodynamic Coefficients of a Subsonic Airplane"

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