TEAMAero - SWBLI
Shock-Wave/Boundary Layer-Interaction (SBLI) is a phenomenon of strong industrial and scientific interest because of the strong, and negative, impact it has in many aeronautical applications and the somehow obscure physics of the problem. The study of SWBLI is studied in the context of the European project TEAMAero (Towards Effective Flow Control and Mitigation of Shock Effects In Aeronautical Applications). Within this framework, 15 Early Stage Researchers (ESRs) from 7 universities, 3 research centres, and 2 companies focus their efforts in investigating SWBLI together with the support of their supervisors and of several industrial partners. Within the project, experimental and numerical studies will be carried on with the aim of gaining a better physical understanding of the problem in the context of turbomachinery and channels for internal aerodynamics and wings for external flows. The project also aims at developing cutting-edge tools for flow characterization through the introduction of new, improved experimental techniques and numerical models. Here at the University of Glasgow, the main attention is devoted to the development and calibration of numerical models for the study of external flows around three-dimensional wings.
PANS for Buffet Flows
The SBLI occurring over the supercritical airfoil OAT15A was studied experimentally by Jacquin et al.  in 2009 at ONERA and represents one of the most detailed experiments in the literature. This test case is investigated by means of Partially averaged Navier-Stokes (PANS) simulations . During the first part of the project, the capability of PANS to adequately reproduce the self-sustained shock oscillation (buffet) occurring on the suction side of the airfoil is assessed. PANS seems promising for its capability to improve the results of URANS even for affordable mesh sizes. Fig. 1 shows the buffet flow for a PANS simulation at AoA = 3.5°, Re = 3e+06, and M = 0.73.
Fig. 1: Shock motion and lift coefficient for the OAT15A airfoil at buffet condition.
The PANS approach showed its applicability as an enhanced, less dissipative version of URANS (fig. 1), that allowed unlocking the flow instability for the case under analysis at no additional cost. On the other hand, if a fine grid is employed, this strategy can be used to perform scale-resolving simulations to focus on the buffet physics (fig. 2)
Fig. 2: Q Criterion (Q=10) iso-surface around the 2D aerofoil with periodic boundary conditions. Pressure isocontour on the background.
The next steps concern the application of the PANS method to three-dimensional configurations, internal SBLI (e.g. pseudo-shock in rectangular channels), and the testing of PANS in conjunction with non-linear correction and four-equation models.
A short project presentation (video) can be found on:
Buffet Onset with RANS-based Criteria
Because of the low frequency of the shock oscillation driving the buffet, a URANS approach may seem the most appropriate to represent the phenomenon. Still, there is no consensus on the capability of URANS to predict the buffet, being this influenced by a number of factors: turbulence modelling, numerical schemes, spatiotemporal discretisation and influence of the wind tunnel geometry. Therefore, scale resolving simulations have become popular in this context. Unfortunately, the associated CPU costs are high.
An accurate and affordable method is required to predict the onset of buffet for a wide of flight conditions. RANS-based criteria were proposed in recent years and only focus on integral or local steady quantities (fig. 3 for an explanation). Even in this case, a big number of steady computations must be carried out. Here, these criteria have been re-proposed in conjunction with an adjoint method to accelerate the buffet boundary tracking.
Fig. 3: RANS-based criteria for the buffet onset estimate using the lift (left) and momentum (centre) coefficients, and the trailing edge pressure coefficient (right).
The algorithm formulated allows recovering the results of the criteria in their standard forms. At the same time, a saving of 50-60% of the CPU time. The algorithm was tested for the OAT15A and NACA0012 aerofoils, for which data on the experimental onset is available. The adopted criteria maintain a conservative nature, since tend to underestimate the onset angle of attack, and are therefore applicable in the industrial design phase.
Scientific Training SC2
The University of Glasgow held the second Scientific Training (SC2) Recent Developments in Computational Fluid Dynamics in the context of TEAMAero. The course covered several CFD methods like Finite Volume Method, Lattice Boltzmann Method, Vortex Methods, Smooth Particle Hydrodynamics and Kinetic Flow Modelling. Theoretical lectures were alternated to practical sessions focused on the implementation of the aforementioned mathematical models. In a joint effort with NUMECA, industrial partner of TEAMAero, a seminar on the industrial application of CFD for rotary wings and turbomachinery was also given.
TEAMAero Social Media Pages
- LinkedIn: https://www.linkedin.com/showcase/h2020-teamaero/
- Twitter: https://twitter.com/h2020_teamaero
 L. Jacquin, P. Molton, S. Deck, B. Maury, and D. Soulevant. Experimental Study of Shock Oscillation over a Transonic Supercritical Profile. AIAA Journal, 47:1985– 1994, 2009.
 S.S. Girimaji and K.S. Abdol-Hamid. Partially-averaged Navier Stokes Model for Turbulence: Implementation and Validation. In AIAA Aerospace Sciences Meeting and Exhibit, Reno, NE, USA, 2005.