Rapid Load Calculations Using an Efficient Unsteady Aerodynamic Solver

Kharlamov, Daniel; Drofelnik, Jernjej; Ronch, Andrea Da; Walker, Scott J.I.

doi:10.2514/6.2018-3621

Cited by 4 publications

(5 citation statements)

References 13 publications

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“…al. and presented in [69]. This chapter details its application to loads estimation and to multi-element wings.…”

Section: High-lift Panel Loads Estimation Using Low-cost Methodsmentioning

confidence: 99%

“…The Southampton multi-fidelity solver can speed up loads calculations on swept wings by up to two orders of magnitude compared to 3D RANS (depending on the case) and with greater accuracy than the VLM, as viscous effects are still captured [69]. Much of the expertise for its development and use is in-house at the University of Southampton [70] [71].…”

Section: Mesh Generation For 2d Multi-element Aerofoilsmentioning

confidence: 99%

“…The Southampton multi-fidelity solver makes use of the α-based correction method, first proposed by Tseng and Lan [76] in 1988. In the Southampton multi-fidelity solver, two fidelity levels of aerodynamic flow prediction are used to obtain rapid estimations of aerodynamic loads in subsonic and transonic flight regimes: low-fidelity three-dimensional effects are modelled via a 3D linear steady and unsteady vortex lattice method solver, while a high-fidelity infinite swept wing RANS/URANS solver (DLR-Tau) is used to capture sectional viscous flow effects [69]. The background to these two solvers is outlined in the next two subsections, and their interaction with each other is via a coupling algorithm, discussed further in Section 5.1.4.…”

Section: Introductionmentioning

confidence: 99%

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High-Lift Actuation Weight Estimation Using Low-Cost Methods

Moss

Ronch

Tyler

2020

AIAA Scitech 2020 Forum

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Faculty of Engineering and Physical Sciences Aeronautical and Astronautical Engineering Doctor of PhilosophyHigh-lift actuation weight estimation using low-cost methods by Benjamin Moss Civil passenger aircraft use high-power actuation systems to deploy high-lift surfaces on the leading and trailing edges of their wings. The mass and size of these systems scales with the expected load the high-lift surfaces are deploy. The problem is that estimated maximum panel loads are not known to a high degree of confidence in the conceptual and preliminary phases of design. The concequence of this in the early phases of the design cycle is that actuation system mass cannot be incorporated to any optimisation loop and traded off against design variables as part of an aerostructural optimisation. This increases uncertainty in the wing weight and the corresponding structural design margins. Ultimately, this uncertainty degrades performance and provides pessimistic estimates of dynamic aeroelastic response.This thesis presents a solution in three parts. First it presents a method for estimating the high-lift actuation system using the aircraft's high-lift geometry. Second, it introduces a novel approach to estimating high-lift panel loads using low cost computational methods suitable for conceptual and preliminary aircraft design. Third, it quantifies the impact of the high-lift actuation system on the dynamic aeroelastic response. vii

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“…al. and presented in [69]. This chapter details its application to loads estimation and to multi-element wings.…”

Section: High-lift Panel Loads Estimation Using Low-cost Methodsmentioning

confidence: 99%

Section: Mesh Generation For 2d Multi-element Aerofoilsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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High-Lift Actuation Weight Estimation Using Low-Cost Methods

Moss

Ronch

Tyler

2020

AIAA Scitech 2020 Forum

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“…The quest for an appropriate mathematical model of aerodynamic loads for flight simulation is a long-standing challenge. A multitude of approaches has been proposed [1,12,13], but the challenge still remains: how to retain unsteady and nonlinear flow effects for applications requiring fast turn-around times, such as in conceptual design? Herein, we leverage on three possible options.…”

Section: A Aerodynamic Modelsmentioning

confidence: 99%

Flying qualities reliability constraints in aircraft conceptual design using time-marching simulations

Saporito

Ronch

Bartoli³

et al. 2021

Aiaa Aviation 2021 Forum

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Aircraft conceptual design, especially when novel concepts are involved, is inherently affected by uncertainty. Although many efforts are done to include more physics at the earliest design phases, often information on impact of the underlying uncertainty is missing. This work proposes an approach to incorporate uncertainty into aircraft conceptual design through reliability constraints on some desired dynamic performance requirements. These are estimated from unsteady time-domain simulations through a system identification process, leveraging on three available aerodynamic fidelity levels. Uncertainty propagation is addressed by a polynomial chaos expansion technique. After presenting the structure and the validation of the proposed framework, a demonstrative application of fuel mass optimization for a transport aircraft under uncertainty is performed, with reliability constraints on short period characteristics.

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“…The elements of the aerodynamic influence coefficient (AIC) matrix are corrected based on Kirchhoff's model for separated flow over a flat plate, where the separation point location is estimated using a semi-empirical model developed by Leishman and Beddoes [66]. Kharlamov et al [67] use a 2D URANS solver modified to obtain solutions for "infinite-swept-wings", which includes the effects of sweep in the lift-curves of the 2D sections of the wing. An α-correction method is used to modify the effective angle of attack of the sections of the wing.…”

Section: Introductionmentioning

confidence: 99%

A Low-Order Method for Prediction of Separation and Stall on Unswept Wings

Hosangadi¹,

Gopalarathnam²

2020

Preprint

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A low-order method is presented for aerodynamic prediction of wings operating at nearstall and post-stall flight conditions. The method is intended for use in design, modeling, and simulation. In this method, the flow separation due to stall is modeled in a vortex-lattice framework as an effective reduction in the camber, or "decambering." For each section of the wing, a parabolic decambering flap, hinged at the separation location of the section, is calculated through iteration to ensure that the lift and moment coefficients of the section match with the values from the two-dimensional viscous input curves for the effective angle of attack of the section. As an improvement from earlier low-order methods, this method also predicts the separation pattern on the wing. Results from the method, presented for unswept wings having various airfoils, aspect ratios, taper ratios, and small, quasi-steady roll rates, are shown to agree well with experimental results in the literature, and computational solutions obtained as part of the current work.

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Rapid Load Calculations Using an Efficient Unsteady Aerodynamic Solver

Cited by 4 publications

References 13 publications

High-Lift Actuation Weight Estimation Using Low-Cost Methods

High-Lift Actuation Weight Estimation Using Low-Cost Methods

Flying qualities reliability constraints in aircraft conceptual design using time-marching simulations

A Low-Order Method for Prediction of Separation and Stall on Unswept Wings

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