Quiet Aerofoils of the Next Generation

Lead Research Organisation: City, University of London
Department Name: Sch of Engineering and Mathematical Sci

Abstract

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Description The research focused on the possibility of adopting noise reducing devices on aerofoil that would not degrade excessively the aerodynamic performance. Through experiments and simulations we have explored a parametric space containing the geometric features of both leading edge undulations and trailing edge serrations. This has led to generate a map that associated lift, drag and a noise reduction metric to allow determining sweet spots on the parametric maps. This outcome was the major deliverable of the project. An extension through an IAA-EPSRC short grant will help in assessing the performance of the developed geometry at higher Reynolds number and at a moderate incidence (similar to the one used in aeronautical landing or take-off operations).
Exploitation Route The implementation of the geometry, once tested in the new Southampton wind tunnel can be eventually tested by Vestas and Airbus.
Sectors Aerospace, Defence and Marine,Energy,Transport
 
Description Started an active collaboration with airbus to study the effects of vortex generators on the leading edge of swept wings for mitigating adverse effects at high loading conditions. The most important outcome is the generation of a solid, multi-expertise research group that kept on collaborating also after the finalization of the project. The team is still collaborating by publishing further articles in common. Moreover our last common proposal (fianced by EPSRC: EP/V006924/1 will spin-off at th
First Year Of Impact 2017
Sector Aerospace, Defence and Marine,Energy,Manufacturing, including Industrial Biotechology,Transport
Impact Types Economic
 
Description Airbus co-financed PhD Scholarship
Amount £40,000 (GBP)
Organisation Airbus Group 
Sector Academic/University
Country France
Start 10/2016 
End 03/2020
 
Description IAA EPSRC aerofoil of the next generation
Amount £48,000 (GBP)
Organisation University of Nottingham 
Sector Academic/University
Country United Kingdom
Start 10/2018 
End 03/2019
 
Title Development of numerical code for the simulation of flows around aerofoils with leading and trailing-edge undulations 
Description New numerical tools are incorporated in our in-house developed numerical code "SUSA". This is an incompressible, finite volume, three dimensional Navier-Stokes equations solver in which the fluxes are approximated by a second-order central formulation and the equations are advanced in time by a second-order semi-implicit fractional-step procedure, where the Crank-Nicolson scheme is used for the wall-normal diffusive terms, and the Adams-Bashforth scheme is employed for all the other terms. The Poisson equations are transformed into wave-number space via Fast Fourier Transform (FFT) and then solved using a preconditioned Krylov method (using PETSc). The code is parallelized using the domain decomposition technique and the MPI message passing library. The new tools incorporated in the code include the Immersed boundary methods (Direct Forcing, Reproducing Kernel Particle Method) for the simulations of flows around complex objects on Cartesian and curvilinear non-conformal grids (like modified aerofoils with leading and trailing edge undulations). Also, new tools have also been developed to simulate the aerofoils with grid-generated incoming turbulence. 
Type Of Material Improvements to research infrastructure 
Year Produced 2011 
Provided To Others? Yes  
Impact These research tools and methods will be helpful in understanding the effects of leading and trailing-edge modifications on the aerodynamic and aeroacoustic performance of the aerofoils. 
 
Title Data from DNS simulations 
Description 1-DNS and LES data of fully separated Low Reynolds (20,000 and 50,000) flow around a NACA-651210 cambered aerofoil. Available data: Time and spanwise averaged statistics are available for pressure and all the components of velocity, their derivatives and Reynolds stresses. The statistics are converged over a long duration of 100 time units (100 flow-throughs over the aerofoil). 2-DNS data of flow around a NACA4412 aerofoil with retrofitted trailing-edge extensions (at Re=100,000). 3 different configurations of trailing-edge extensions have been investigated along with the baseline simulation. Available data: Around 400 instantaneous volumetric fields are available for each configuration which spans over 65 flow-throughs over the serrations. In addition, statistically converged volumetric data is also available for pressure and all the components of velocity, their derivatives and Reynolds stresses. 
Type Of Material Database/Collection of data 
Year Produced 2017 
Provided To Others? Yes  
Impact The first database would be helpful in understanding the dynamics of Low Reynolds number fully separated flow regime in off-design conditions. Especially, the unsteady evolution of the wake evolution and the shear layer development. The second database provides valuable volumetric flow information about the aerofoils with trailing-edge undulations and their impact on the hydrodynamic characteristics of the turbulent wake and the upstream boundary layer. This information would help us to design quiet aerofoils for the next generation. 
 
Description KTH 
Form Of Engagement Activity A formal working group, expert panel or dialogue
Part Of Official Scheme? No
Geographic Reach International
Primary Audience Postgraduate students
Results and Impact Invitation received in participating in a KTH organised summer school. Participant only by invitation interacting with PhD students, post docs and researchers from UK, Sweden, US, Brazil, Korea....
Year(s) Of Engagement Activity 2018
URL https://www.flow.kth.se/event/transep-research-program-in-stability-transition-and-control-kth-4-15-...