Anastasios S. Lyrintzis

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An approach for parallelizing the three-dimensional Euler/Navier-Stokes rotorcraft computational fluid dynamics flow solver transonic unsteady rotor Navier-Stokes (TURNS) is introduced. Parallelization is performed using a domain decomposition technique that is developed for distributed-memory parallel architectures. Communication between the subdomains on(More)
This paper compares two methods for predicting transonic rotor noise for helicopters in hover and forward ight. Both methods rely on a computational uid dynamics (CFD) solution as input to predict the acoustic near and far elds. For this work, the same full-potential rotor code has been used to compute the CFD solution for both acoustic methods. The rst(More)
A parallel genetic algorithm (GA) was used to generate, in a single run, a family of aerodynamically efficient, low-noise rotor blade designs representing the Pareto optimal set. The n-branch tournament, uniform crossover genetic algorithm operates on twenty design variables, which constitute the control points for a spline representing the airfoil surface.(More)
Recent advances in materials science and actuation technologies have led to interest in morphing aircraft. The research discussed in this paper focuses upon the shape design of morphing airfoil sections. In the efforts herein, the relative strain energy needed to change from one airfoil shape to another is presented as an additional design objective along(More)
This paper presents the results of using high-order compact schemes with a high-order filter on multi-block domains. The Linearized Euler Equations (LEE) are solved on a uniform mesh for benchmark problems in one and two dimensions. Also a two dimensional mixing layer is solved by using LargeEddy Simulation (LES). Three different boundary schemes are(More)
The performance of two popular turbulence models, the Spalart-Allmaras model and Menter’s SST model, and one relatively new model, Olsen & Coakley’s Lag model, are evaluated using the OVERFLOW code. Turbulent shock-boundary layer interaction predictions are evaluated with three different experimental datasets: a series of 2D compression ramps at Mach 2.87,(More)
The modiŽ cation of unsteady three-dimensional Navier–Stokes codes for application on massively parallel and distributed computing environments is investigated. Previously, the Eulermode of the Navier–Stokes code TURNS has been parallelized. For the efŽ cient implementationof theNavier–Stokesmode of TURNS onparallel computing systems, several algorithmic(More)
Computational aeroacoustics (CAA) has emerged as a tool to complement theoretical and experimental approaches for robust and accurate prediction of sound levels from aircraft airframes and engines. CAA, unlike computational fluid dynamics (CFD), involves the accurate prediction of small-amplitude acoustic fluctuations and their correct propagation to the(More)