This thesis extended the order of the reconstruction of state for convective fluxes used by Finite Volume (FV) algorithm in DLR’s next-generation CFD solver: Flucs, from constant and linear to quadratic and cubic. Two approaches for calculating derivatives were implemented in Flucs and some test cases were tried. To allow for integration of moments within each cell and a higher-order integratio...

The present work focuses on the comparison of numerical simulation sheet/cloud cavitation with Reynolds Average Navier-Stokes and Large Eddy Simulation(RANS LES) methods around NACA0012 hydrofoil in water flow. Three kinds turbulence models—SST k-?, modified SST Smagorinsky’s model—were used this paper. unstable sheet cavity periodic shedding were predicted, results, namelycavitation shape, fre...

With stratospheric flight or martian exploration in perspective, the compressibility influence on wake dynamics of a NACA0012 profile is investigated. The unsteady flow past airfoil at characterized using direct numerical simulations for various angles attack and Mach numbers up to . Steady flows obtained selective frequency damping (SFD) technique are used as base states global linear stabilit...

For the numerical resolution of the compressible Navier-Stokes equations (NS) with Finite Volumes (FV) two main approaches have called the attention of researchers and engineers. First, following the hyperbolic nature of the compressible NS equations, the Godunov-like schemes discretize the numerical fluxes by a characteristic analysis. Second, disregarding the hyperbolicity of the equations, t...

This study investigated the performance of symmetric airfoils type NACA0012 numerically under different operating conditions. It has been assumed that involves steady state, non-compressive, and turbulent flows. The fluid was air. effect Reynolds number angle attack on lift drag coefficients, pressure distribution, velocity distribution investigated. ANSYS FLUENT used to solve numerical model b...

Adjoint method is widely used in aerodynamic design because only once solution of flow field required for it to obtain the gradients all variables. However, computational cost adjoint vector approximately equal that computation. In order accelerate and improve efficiency adjoint-based optimization, machine learning modeling presented. Deep neural network (DNN) employed construct mapping between...

A parametric investigation of the influence a small cylinder on laminar separated boundary layer over NACA0012 wing is performed using numerical simulations. The (γ - Reθ,t) steady RANS transitional model first validated in capturing separation baseline suction surface. effects three rod diameter ratios (d/c = 0.67%, 1.33% and 2%) bubble aerodynamic performances were examined. qualitative analy...

The aim of this experimental study is two-dimensional investigation of cargo behavior after separation which is carried out in the subsonic wind tunnel. Given that the real separation occurs in three-dimension, the results of this study may be widely used in numerical aerodynamic studies for verification of new computational methods and they can be used as the reference results in this area. So...