Analysis of Resolved Turbulent Scales of Motion in Aeroelastic Problems

Righi, Marcello; Ronch, Andrea Da; Mazzacchi, Francesco

doi:10.2514/6.2017-0189

Cited by 3 publications

(1 citation statement)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The surface signature and structure of the vortices forming over the canard and main wing are shown in Figure 8 for various angles of attack. Above ␣ ϭ 20.0°, the flow presents massively separated regions that are not modelled properly with a RANS model, requiring higher fidelity in the flow modelling as well as resolving the important unsteady effects in the flow (Righi et al, 2017).…”

Section: Validation At Wind Tunnel Flow Conditionsmentioning

confidence: 99%

Adaptive design of experiments for efficient and accurate estimation of aerodynamic loads

Ronch

Panzeri

Bari

et al. 2017

Aircraft Eng & Aerospace Tech

Self Cite

View full text Add to dashboard Cite

Aerodynamic design, which aims at developing the outer shape of the aircraft while meeting several contrasting requirements, demands an accurate and reliable aerodynamic database. Computing forces and moments with the highest level of delity is a prerequisite, but practically limited by wall clock time and available computing resources. An ecient and robust approach is therefore sought after. This study investigates two design of experiments algorithms in combination with surrogate modelling. In traditional design of experiments, the samples are selected a priori before running the numerical explorative campaign. It is wellknown that this may result in either poor prediction capabilities or high computational costs. The second strategy employs an adaptive design of experiments algorithm. As opposed to the former, this is a selflearning technique that iteratively: i) identies the regions of the design space that are characterised by stronger nonlinearities; * First corresponding author. Email: A.Da-Ronch@soton.ac.uk Preprint submitted to SCAD 2016 August 10, 2016 and ii) select the new samples in order to maximise the information content associated with the simulations to be performed during the next iteration. In this work, the Reynoldsaveraged NavierStokes equations are solved around a complete aircraft conguration. A representative ight envelope is created taking the angle of attack and Mach number as design parameters. The adaptive strategy is found to perform better than the traditional counterpart. This is quantied in terms of the sum of the squared error between the surrogate model predictions and CFD results. For the pitch moment coecient, which shows strong nonlinearities, the error metric using the adaptive strategy is reduced by about one order of magnitude compared to the traditional approach. Furthermore, the proposed adaptive methodology, which is employed on a high performance computing facility, requires no extra costs or complications than a traditional methodology.

show abstract

Section: Validation At Wind Tunnel Flow Conditionsmentioning

confidence: 99%