Inviscid drag prediction for transonic transport wings using a full-potential method

Vooren, Jean‐Paul Van; Wees, A.J. van der

doi:10.2514/3.46111

Cited by 7 publications

(1 citation statement)

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“…The estimation of viscous drag is obtained through the coupling with a boundary-layer solver. Wave drag is characterised by the volume integration of the artificial viscosity [50]. When considering data regarding wing twist under a 1g load in A320-200 aircraft in [51], FEMWET presents an error of −0.12% in the wing weight calculation, considering an aeroelastic optimisation that provides the thickness of the equivalent panels.…”

Section: Validationmentioning

confidence: 99%

Investigations on the Potentials of Novel Technologies for Aircraft Fuel Burn Reduction through Aerostructural Optimisation

Mosca

Elham

2022

Aerospace

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A physics-based optimisation framework is developed to investigate the potential advantages of novel technologies on the energy efficiency of a midrange passenger aircraft. In particular, the coupled-adjoint aerostructural analysis and optimisation tool FEMWET is modified to study the effects of active flow control at different load cases for conventional and unconventional wing configurations. This multidisciplinary design optimisation (MDO) framework presents the opportunity to optimise the wing considering static aeroelastic effect and, by its gradient-based method, save substantial computational time compared to high-fidelity tools, keeping a satisfying level of accuracy. Two different configurations are analysed: a forward- and backward-swept wing aircraft, developed inside the Cluster of Excellence SE2A (Sustainable and Energy-Efficient Aviation). The forward-swept configuration is sensitive to the aeroelastic stability effect, and the backward configuration is influenced by the aileron constraint. They may lead to a weight increment. Sensitivity studies show the possible role of key parameters on the optimisation results. The highest fuel weight reduction achievable for the two configurations is 5.6% for the forward-swept wing and 9.8% for the backward configuration. Finally, both optimised wings show higher flexibility.

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Section: Validationmentioning

confidence: 99%