1,720,975 research outputs found
Effects of a trapped vortex cell on thick wing profile
Full text linkExperimental investigation on the effects originated from a trapped vortex cell on the NACA0024 airfoi
Application of the ray-tracing theory to the stability analysis of three-dimensional compressible boundary layers
No full textReport on detailed review of wind tunnel data
No full textControllo del flusso attorno al profilo alare NACA0024 mediante la tecnica del " trapped vortex cell" al fine di migliorare le prestazioni aerodinamiche del profilo alare
Improving aircraft endurance through turbolent separation control by pulsed blowing
No full textBoundary layer unsteady blowing is one of the most advanced solutions for reducing aircraft parasite drag and flow separation at high angles of attack. This allows high lift along with low-drag to be achieved and since endurance is one of the most important performance parameters for certain types of aircraft, such as UAVs, clearly the CL3/2/CD ratio has to be maximized. The main goal of the present investigation is to explore possible ways to obtain efficient turbulent boundary layer control, and at the same time to consider the practical problems connected to the installation of the device in a real wing. This study seeks mainly to verify the effectiveness of active control via pulsed blowing as a tool to delay boundary layer separation. Numerical simulations and wind tunnel experimental investigations on a wing model equipped with instruments are presented and the results discussed
Summary of wind tunnel tests, preliminary analysisVCell 2050 - VI EU Program. Contract No: AST4-CT-2005-012139. Deliverable 8.2.10 – December 2009
No full textControllo del flusso attorno al profilo alare NACA0024 mediante la tecnica del "trapped vortex cavity" al fine di migliorare le prestazioni aerodinamiche del profilo alare
A Hybrid Model based on POD and Domain Decomposition to Compute the 2-D Aerodynamics Flow Field
No full textImproving aircraft endurance through turbulent separation control
No full textBoundary layer unsteady blowing is one of the most advanced solutions for reducing aircraft parasite drag and flow separation at high angles of attack. This allows high lift along with low-drag to be achieved and since endurance is one of the most important performance parameters for certain types of aircraft, such as UAVs, clearly the CL3/2/CD ratio has to be maximized. The main goal of the present investigation is to explore possible ways to obtain efficient turbulent boundary layer control, and at the same time to consider the practical problems connected to the installation of the device in a real wing. This study seeks mainly to verify the effectiveness of active control via pulsed blowing as a tool to delay boundary layer separation. Numerical simulations and wind tunnel experimental investigations on a wing model equipped with instruments are presented and the results discussed
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