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Download Drag Reduction by Shock and Boundary Layer Control: Results by Egon Stanewsky, J. Delery, John Fulker, Paolo de Matteis PDF

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By Egon Stanewsky, J. Delery, John Fulker, Paolo de Matteis

This quantity features a thorough description of the EU-supported venture EUROSHOCK II occupied with the research of lively surprise and boundary layer regulate to enhance plane functionality. mentioned are uncomplicated experiments, supplemented by means of Navier-Stokes computations, to enhance and validate actual types correct to manage and the extension, validation and alertness of varied computational tips on how to airfoil and wing flows with keep an eye on. moreover defined are experiments on airfoils and wings performed to evaluate the aerodynamic merits of keep watch over and to supply information for validation reasons. ultimately, regulate purposes to genuine plane and the corresponding deploy consequences and venture advantages are addressed. This quantity is a sequel to Vol. fifty six on passive surprise control.

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Read or Download Drag Reduction by Shock and Boundary Layer Control: Results of the Project EUROSHOCK II. Supported by the European Union 1996–1999 PDF

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Extra info for Drag Reduction by Shock and Boundary Layer Control: Results of the Project EUROSHOCK II. Supported by the European Union 1996–1999

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The Johnson-King model and the Spalart-Allmaras model, respectively. Provisions to treat the control mechanisms considered here have been implemented by INTA. , below the buffet boundary, and will automatically provide unsteady oscillatory results as soon as the buffet process commences; it can therefore be employed to directly determine the buffet boundary. 10]: The Viscous-Inviscid Interaction (VII) codes, namely the steady code VIS05c and the unsteady code VIS15, have been utilized to compute airfoil flow with shock control.

The code is able to distinguish between a steady and an unsteady solution and can, therefore, be used to determine the buffet boundary. For the computation of the quasi-3D infinite swept-wing flow, the unsteady code VIS25 has been employed which is a direct extension of the 2D code VIS15 adapted to sheared-wing conditions. I1]: The in viscid flow field is computed by solving the Euler equations on a structured grid following the scheme of Schmidt, Jameson and Turkel. The method is based on a central space discretization with explicit adaptive artificial dissipation.

We have hence considered local flow developments as affected by shock and boundary layer control which, of course, strongly shape the global developments associated with airfoil and wing flow. The control mechanisms studied were: 36 • • • • Active control by means of a perforated plate / cavity arrangement with partsuction including the "zero-suction" passive control case. Hybrid control, consisting of a passive cavity in the shock region and suction, either through a cavity covered by a perforated plate or a slot, downstream.

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