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In the age of globalization, commercial aviation plays a central role in maintaining our international connectivity by providing fast air transport services for passengers and freight. However, the upper limit of the aircraft flight envelope, i.e., its operational limit in the high-speed regime, is usually fixed by the occurrence of an aerodynamic phenomenon called transonic airfoil buffet. It refers to shock wave oscillations occurring on the aircraft wings, which induce unsteady aerodynamic loads acting on the wing structure. Since these loads can cause severe structural damage endangering flight safety, the aviation industry is highly interested in suppressing transonic airfoil buffet to extend the flight envelope to higher aircraft speeds. In this contribution, we demonstrate experimentally that the application of porous trailing edges substantially attenuates the buffet phenomenon. Since porous trailing edges have the additional benefit of reducing acoustic aircraft emissions, our findings could pave the way for faster air transport with reduced noise emissions.

Broadband noise reduction is a significant problem in aerospace and industrial applications. Specifically, the noise generated from the trailing edge of an airfoil poses a challenging problem with various proposed solutions. This study investigates the porous trailing edge treatment. We use surrogate-based gradient-free optimization and an empirical noise model to efficiently explore the design space and find the optimal porosity distribution. As a result, a predicted 8-10 dB reduction in the broadband 300-5000 Hz was achieved. Furthermore, the optimal design emphasizes the design space's complexity and global exploration's difficulty. Further, the optimal design presents a low porous solution while constituting significant noise reduction., Comment: 5 pages, 6 figures, added affiliation, fixed typos, homog. citation style

The transonic flow around the OAT15A airfoil is computed at buffet conditions, i.e., freestream Mach number $Ma_\infty = 0.73$, chord-based freestream Reynolds number $Re_c = 2\cdot10^6$, and angle of attack $\alpha = 3.5^\circ$ using wall-modeled LES. Two configurations are considered, one which includes a generic ultra-high bypass ratio (UHBR) engine nacelle geometry and one without an engine, which is denoted the baseline case. The introduction of the UHBR-engine nacelle leads to a significant deviation of the flow onto the airfoil from the baseline case and has an essential effect on the occurring shock dynamics. The flow field of the nacelle configuration is characterized by a shock wave on the upper part of the nacelle sharing dynamic features with the shock on the airfoil. This impact of the nacelle shock on the airfoil shock means a reduced strength of the airfoil shock resulting in a less developed buffet. The perturbation of the general flow field is evaluated as to established buffet models and the dynamic features of the shock waves are analyzed by the sparsity-promoting dynamic mode decomposition. This analysis shows the existence of a shared dynamic mode of the nacelle and the airfoil shock which suggests a coupling mechanism between them.

We are interested in the development of an algorithmic differentiation framework for computing approximations to tangent vectors to scalar and systems of hyperbolic partial differential equations. The main difficulty of such a numerical method is the presence of shock waves that are resolved by proposing a numerical discretization of the calculus introduced in Bressan and Marson [Rend. Sem. Mat. Univ. Padova, 94:79-94, 1995]. Numerical results are presented for the one-dimensional Burgers equation and the Euler equations. Using the essential routines of a state-of-the-art code for computational fluid dynamics (CFD) as a starting point, three modifications are required to apply the introduced calculus. First, the CFD code is modified to solve an additional equation for the shock location. Second, we customize the computation of the corresponding tangent to the shock location. Finally, the modified method is enhanced by algorithmic differentiation. Applying the introduced calculus to problems of the Burgers equation and the Euler equations, it is found that correct sensitivities can be computed, whereas the application of black-box algorithmic differentiation fails.