Special Issue "Modelling of Aircraft Unsteady and Nonlinear Aerodynamics"

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (31 October 2020) | Viewed by 1911

Special Issue Editor

Prof. Mikhail Goman
E-Mail Website
Guest Editor
School of Engineering and Sustainable Development, De Montfort University, Leicester LE1 9BH, UK
Interests: aerodynamics modelling; nonlinear flight dynamics; flight simulation; Loss-Of-Control In flight (LOC-I)

Special Issue Information

Dear Colleagues,

The mathematical modelling of aerodynamic forces and moments acting on aircraft, when solving flight dynamics and/or flight simulation problems, is normally formulated in the form of an autonomous block, with flight parameters on its entry and aerodynamic coefficients on its output. A standard practice is when the representation of aerodynamic coefficients is made in a linear form using so called aerodynamic derivatives, or is based on look-up data tables with a linear interpolation reflecting the nonlinear dependence of the aerodynamic coefficients on the flight parameters. The required data for the modelling of steady and unsteady aerodynamic responses are usually experimentally received in wind tunnels using static and dynamic techniques. The complementary use of computational methods for predicting aerodynamic responses leads to an increased fidelity of aerodynamic modelling.

A more adequate phenomenological approach for aerodynamic modelling is required for flight at high angles of attack, characterised by the onset of flow separation. There is a need for running an adequate simulation of the loss-of-control in flight (LOC-I) happening in the stall region, so as to allow pilots' training for upset prevention and recovery. A similar modelling is required for the design of the control laws for aircraft flight envelope protection/expansion, for the active control of flow separation on wind turbine blades, etc.

Both experimental and computational predictions of aerodynamic loads in the stall region are very sensitive to a number of usually minor factors. For example, wind tunnel results are sensitive to the level of flow turbulence and the structural vibrations of the tested model. Computational results strongly depend on the choice of a turbulence model and its parameters used for the closure of the Reynolds Averaged Navier–Stokes Equations (URANS) and the type of solver. A joint analysis of the experimental and computational results may help to develop justifiable adequate aerodynamic modelling methods important for the accurate prediction of the aerodynamic hysteresis phenomenon in static and dynamic conditions.

This Special Issue entitled “Modelling of Aircraft Unsteady and Nonlinear Aerodynamics” aims to present the latest results in the area of modelling of stall aerodynamics considering experimental, computational, and phenomenological modelling methods.

Prof. Mikhail Goman
Guest Editor

Manuscript Submission Information

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Published Papers (1 paper)

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Numerical Simulations on Unsteady Nonlinear Transonic Airfoil Flow
Aerospace 2021, 8(1), 7; https://doi.org/10.3390/aerospace8010007 - 29 Dec 2020
Cited by 1 | Viewed by 1268
Large-amplitude excitations need to be considered for gust load analyses of transport aircraft in cruise flight conditions. Nonlinear amplitude effects in transonic flow are, however, only marginally taken into account. The present work aims at closing this gap by means of systematic unsteady [...] Read more.
Large-amplitude excitations need to be considered for gust load analyses of transport aircraft in cruise flight conditions. Nonlinear amplitude effects in transonic flow are, however, only marginally taken into account. The present work aims at closing this gap by means of systematic unsteady Reynolds-averaged Navier-Stokes simulations. The RAE2822 airfoil is analyzed for a variety of sinusoidal gust excitations at different transonic Mach numbers. Responses are evaluated with respect to lift and moment coefficients, their derivatives and the unsteady shock motion. A strong dependency on inflow Mach number and excitation frequency is observed. Generally, amplitude effects decrease with lower Mach numbers or higher excitation frequencies. The unsteady nonlinear simulations predict lower maximum lift values and lower lift and moment derivatives compared to their linear counterparts for lower frequencies in combination with large-amplitude excitations. For the mid-frequency range, trends are not as clear. Additionally, it is shown that the variables of harmonic distortion and maximum shock motion might not be reasonable indicators to predict a nonlinear response. Full article
(This article belongs to the Special Issue Modelling of Aircraft Unsteady and Nonlinear Aerodynamics)
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