Unsteady Aerodynamic Model Generation in the Frequency Domain

Gebert, Glenn; Dunworth, Kevin; Evers, Johnny

doi:10.2514/6.2003-4087

Cited by 1 publication

(1 citation statement)

References 7 publications

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“…[13][14][15][16] Early in 1975, the static aerodynamic characteristics of F-4D fighter airplane was modeled by Monfort et al 17 Peterson et al 18 utilized a neural network to describe the aerodynamic parameters of F-15 SMTD (STOL (Short Take-off and Landing) and Maneuver Technology Demonstrator) aircraft. A frequencydomain model to compute the aerodynamic forces for an arbitrary and periodic wing motion was devised in a flapping free-flight simulation by Gebert et al 19 Later, a review of the unsteady aerodynamic modeling for the flight dynamics of maneuverable aircrafts was given by Greenwell. 20 In addition, the aerodynamic optimization of a near-sonic passenger plane using the genetic algorithm combined with the Euler simulations have been carried out by Watanabe et al 21 The aerodynamic and aerothermodynamic trade-off analysis aiming to design a small hypersonic flying test bed with a relatively simple vehicle architecture was carried out by Pezzella.…”

Section: Introductionmentioning

confidence: 99%

Modeling of unsteady aerodynamic characteristics at high angles of attack

Dong

Zhang

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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An improved model to express the unsteady aerodynamic characteristics at high angles of attack is presented in this paper. The proposed aerodynamic model is expressed on the basis of a progressive state-space representation and Taylor’s series expansion. The state-space expression is a first-order differential equation in which the power item of the angular rate of attack is introduced. The unsteady aerodynamic coefficients are described by Taylor’s series expansion in terms of input variables. The approach of minimum mean square error criterion is utilized to identify the unknown parameters of the proposed model by nonlinear least square method from the tunnel data. The given modeling method is experimentally demonstrated by the wind tunnel measurements of NACA 0015 airfoil with constant rate to high angles of attack, F18 aircraft with constant pitch rate ramp motion, and F18 HARV (high alpha research vehicle) configuration with large-amplitude harmonic oscillatory. The results show that it is possible to analyze more complex unsteady aerodynamic problems for an aircraft within the framework of the proposed aerodynamic model and the represented model is directly amenable to the simulation and control system design.

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