the current study presents the results of the aerodynamic noise prediction of the flow field around a naca 0012 airfoil at a chord-based reynolds number of 100,000 and at 8.4 degree angle of attack. an incompressible large eddy simulation (les) turbulence model is applied to obtain the instantaneous turbulent flow field. the noise prediction is performed by the ffowcs williams and hawkings (fw-...

boundary layer growth and hence displacement thickness are the key factors in shock position over aerodynamical surfaces at transonic regimes. since boundary layer growth is a function of free stream reynolds number and also of the transition location, the free stream reynolds number and also the other parameters involved in the boundary layer growth and its transition location are determinant ...

The current study presents the results of the aerodynamic noise prediction of the flow field around a NACA 0012 airfoil at a chord-based Reynolds number of 100,000 and at 8.4 degree angle of attack. An incompressible Large Eddy Simulation (LES) turbulence model is applied to obtain the instantaneous turbulent flow field. The noise prediction is performed by the Ffowcs Williams and Hawkings (FW-...

Data previously obtained for the X-33 in the NASA Langley Research Center 20-Inch Mach 6 Air Tunnel have been reanalyzed to compare methods for determining boundary layer edge conditions for use in transition correlations. The experimental results were previously obtained utilizing the phosphor thermography technique to monitor the status of the boundary layer downstream of discrete roughness e...

We study the transition to turbulence in a flat plate boundary layer by means of visibility analysis velocity time-series extracted across flow domain. By taking into account mutual sampled values, graphs are constructed from each time series. The latter are, thus, transformed geometrical object, whose main features can be explored using measures typical network science that provide reduced ord...

Scale Effects on Oscillatory Control-Surfeoe Derivatives-By-A. Y/. Moore Aerod.ynsmlcs Division NPL The limited evidence availahle concerning scale effects on Control-surface derivatives suggests a general tendency for in-phase hinge-moment derivatives to increase when Reynolds number increases but to decrease sharply when boundary-layer transition is artificially fixed. Damping (in-quadrature)...

Transition from laminar flow to turbulent flow occurs very often and plays a crucial role in many practical engineering flows. There are many different kinds of transition and broadly speaking they can be classified into three categories: classical transition in attached boundary; bypass transition in attached boundary layer and separated boundary layer transition. This paper presents a compara...

in this research, shock wave motion, shock/boundary layer interaction, and flow separation in a transonic flow over a naca0012 airfoil were investigated experimentally. thirteen kulite sensors were utilized for measurement of pressure fluctuations over the airfoil. experiments were performed for angles of attack between -4 to 4 degrees and flow mach numbers of m= 0.39 to 0.82. the kulite sensor...