TEAMAero - SWBLI

The Project

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 centers, 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.  

Application of PANS to Buffet Flows

The SBLI occurring over the supercritical airfoil OAT15A was studied experimentally by Jacquin et al. [1] 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 [2]. 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 pressure isocontours and the aerodynamic coefficients over time for a PANS simulation at AoA = 3.5°, Re = 3e+06, and M = 0.73. 

Fig. 1: PANS pressure isocontour and aerodynamic coefficients for the OAT15A airfoil at AoA=3.5°.

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. An accurate and affordable method is required to predict the onset of buffet for a wide of flight conditions. Therefore, together with PANS, the possibility to use methods like adjoint methods, harmonic balance methods, and continuation methods will be explored.

References

[1] 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.

[2] 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.

 

CONTACTS

George N. Barakos, Professor - George.Barakos@glasgow.ac.uk 

Rene Steijl, Senior Lecturer - Rene.Steijl@glasgow.ac.uk

Andrea Petrocchi, PhD Student (PGR) - a.petrocchi.1@research.gla.ac.uk