By Egon Stanewsky, J. Delery, John Fulker, Paolo de Matteis
This quantity features a thorough description of the EU-supported venture EUROSHOCK II curious about the research of energetic surprise and boundary layer keep an eye on to enhance airplane functionality. mentioned are simple experiments, supplemented by way of Navier-Stokes computations, to enhance and validate actual versions proper to manage and the extension, validation and alertness of assorted computational the way to airfoil and wing flows with keep watch over. in addition defined are experiments on airfoils and wings conducted to evaluate the aerodynamic merits of regulate and to supply info for validation reasons. eventually, keep an eye on functions to actual airplane and the corresponding deploy consequences and undertaking advantages are addressed. This quantity is a sequel to Vol. fifty six on passive surprise control.
Read Online 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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Additional resources for Drag Reduction by Shock and Boundary Layer Control: Results of the Project EUROSHOCK II. Supported by the European Union 1996–1999
Example text
Finally, ways must be found to incorporate potential control methods into existing and/or new wing designs and benefits and penalties that can be expected from an incorporation of control into aircraft must be assessed. 2 Detailed Flow Investigations Task 4 Assessment of Controll Control Application Aspects Task 1: Modeling of Active Control Phenomena Task 2: Prediction of Transonic Airfoil I Wing Flow with Control Task 3: Wind Tunnel Experiments on Airfoils and Sheared Wings with Control Task 4: Control Application Aspects Figure 8 General task flow chart and interrelation between tasks 11 3 Modeling of Active Control Phenomena (Task 1) The objective of the work performed here was to further the understanding and modeling of the physical phenomena involved in transonic shock boundary layer interactions under active control conditions.
2 mm x 240 mm with grid refinements at the walls and throughout the interaction region. A relation for the velocity normal to the wall within the control region was derived from a number of experiments in a calibration rig, without, however, accounting for an outer tangential flow as in the case of the Karlsruhe law, something that should be considered in future work. In the calculations three turbulence models, namely, Cebeci-Smith, Baldwin-Lomax and Johnson-King, were used and compared. 3] and Chapters 11, 12, and 13, respectively.
Supplementing the experiments, 20 and 30 Navier-Stokes computations, simulating the channel-flow experiments, were performed. Cambridge University considered active shock and boundary layer control in three-dimensional flows with the control mechanisms considered being a perforated plate / cavity arrangement with part-suction, and discrete slot suction with emphasis on the effect of the slot location with respect to the shock. Again, Navier-Stokes computations, using different turbulence models, supplemented the swept-shock channel-flow experiments.