State-space representation of aerodynamic characteristics of an aircraft at high angles of attack

Goman, Mikhail; Храбров, А. Н.

doi:10.2514/3.46618

Cited by 372 publications

(185 citation statements)

References 10 publications

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“…The time domain models are based on the state space representation by matching time histories of measured data. Some examples of time domain ROMs include the unit sample response [15,57,49,18], Volterra theory [56,55,54,9], Radial Basis Functions (RBF) [29,19,7] and state-space modeling [20,32]. In this paper, the mathematical model of indicial functions, Radial Basis Functions, and state-space method are presented.…”

Section: Reduced-order Aerodynamic Modelsmentioning

confidence: 99%

“…A state space model detailed by Goman and Khrabov [21] is considered in this work. In this approach, the unsteady aerodynamic loads are found from an input-output dynamical system in the form of: (27) where, u shows the system input vector and defined in Eq.…”

Section: State Space Modelingmentioning

confidence: 99%

“…In this approach, the unsteady aerodynamic loads are found from an input-output dynamical system in the form of: (27) where, u shows the system input vector and defined in Eq. (20), C j denote aerodynamic forces that for pitching and plunging motions are j = L, D, m. x is a non-dimensional coordinate which describes the flow separation point on the upper surface of airfoil as shown in Fig. 4, such that x = 1 refers to the attached flow, and x = 0 means flow separation point is at the leading edge.…”

Section: State Space Modelingmentioning

confidence: 99%

See 2 more Smart Citations

Challenges in the aerodynamics modeling of an oscillating and translating airfoil at large incidence angles

Ghoreyshi

Cummings

2013

Aerospace Science and Technology

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The challenges in the modeling of the unsteady lift of a two-dimensional NACA 0012 airfoil oscillating and translating at large incidence angles are investigated in this paper. Forced oscillation motions with two reduced frequency values of 0.1 and 1.0 were used. The CFD results show that a hysteresis loop was developed in the lift variation with angle of attack; shapes of the loops change significantly with reduced frequency value. A dynamic stall vortex was identified in the pitching and plunging motions with k = 0.1.This vortex delays the onset of flow separation over the upper surface to a higher incidence than would occur in steady conditions. The unsteady lift of the very fast motion is enhanced significantly due to the formation of a compression wave on the lower surface and an expansion wave on the upper surface. The results show clear limitations of unsteady aerodynamic theories for modeling motions at high incidences. Also, the CFD solution of indicial functions show a large oscillation at angles of attack beyond the stall angle, but the predictions of a model based on Radial Basis Function matches CFD values quite well.

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Section: Reduced-order Aerodynamic Modelsmentioning

confidence: 99%

Section: State Space Modelingmentioning

confidence: 99%

Section: State Space Modelingmentioning

confidence: 99%

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Challenges in the aerodynamics modeling of an oscillating and translating airfoil at large incidence angles

Ghoreyshi

Cummings

2013

Aerospace Science and Technology

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“…The next step in developing the aerodynamic models was made by Goman and his colleague [51,52]. They had formulated the aerodynamic coefficient models in the form of a state space representation:…”

Section: Developed Aerodynamic Modelsmentioning

confidence: 99%

Goal- and Object-Oriented Models of the Aerodynamic Coefficients

Rohács¹

2018

Flight Physics - Models, Techniques and Technologies

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Nowadays, aeronautics discovers new ways of flights near the critical regimes, unconventional aircraft forms, utilizing the micro-electro-mechanical technologies in flow and aircraft control, adaptive and morphing structures, using the structures and controls based on the biological principles, developing highly flexible structures, etc. Before deployment, these new technologies and solutions must be evaluated, tested in wide aerodynamic, flight dynamic simulations that require improved and new type of aerodynamic coefficient models. The chapter overviews the applicable models of the aerodynamic coefficients, introduces some new models and demonstrates how the different models can be applied in different goal-and object-oriented solutions. The following will be shortly explained: (i) how the aerodynamic forces and moments are generating, (ii) how the linear, nonlinear, steady, and nonsteady aerodynamic coefficient structures and forms might be modeled, and (iii) how to harmonize the model with the goal and object of investigations.

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“…Kirchoff's zone of constant pressure formulation may be used to establish the location of flow separation [9]. The lift coefficient can be expressed as:…”

Section: Theoretical Developmentmentioning

confidence: 99%

Semi-Empirical Prediction of Airfoil Hysteresis

Traub

2016

Aerospace

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A semi-empirical method is presented to estimate the angular excursion and the lift loss associated with static hysteresis on an airfoil. Wind tunnel data of various airfoils is used to define and validate the methodology. The resulting equation provides a relationship between the size of the hysteresis loop and characteristics of the airfoil. Comparisons of the equation with experiment show encouraging agreement both in terms of the magnitude of the lift loss and the extent of the loop.

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State-space representation of aerodynamic characteristics of an aircraft at high angles of attack

Cited by 372 publications

References 10 publications

Challenges in the aerodynamics modeling of an oscillating and translating airfoil at large incidence angles

Challenges in the aerodynamics modeling of an oscillating and translating airfoil at large incidence angles

Goal- and Object-Oriented Models of the Aerodynamic Coefficients

Semi-Empirical Prediction of Airfoil Hysteresis

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