By Dietrich Knörzer (auth.), Prof. Dr.-Ing. Peter Thiede (eds.)
------------------------------------------------------------ This quantity includes the lawsuits of the CEAS/DragNet eu Drag relief convention hung on 19-21 June 2000 in Potsdam, Germany. This convention, succeeding the ecu Fora on Laminar circulate expertise 1992 and 1996, was once initiated by means of the eu Drag relief community (DragNet) and organised by means of DGLR below the auspice of CEAS. The convention addressed the hot advances in all parts of drag relief study, improvement, validation and demonstration together with laminar circulate expertise, adaptive wing thoughts, turbulent and triggered drag relief, separation keep an eye on and supersonic movement facets. This quantity which includes greater than forty convention papers is of specific curiosity to engineers, scientists and scholars operating within the aeronautics undefined, examine institutions or academia.
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Additional resources for Aerodynamic Drag Reduction Technologies: Proceedings of the CEAS/DragNet European Drag Reduction Conference, 19–21 June 2000, Potsdam, Germany
For several of the examples cited here, this last step is now on the way. This historical survey, elaborated with the help of Volker Schmitt from ONERA, is far from being exhaustive. I shall focus on the main efforts made in France and in Europe. Airbus competition, very little information is available from the US. ,/' ( \ Basic research -- Theory Numerical simulation ___Experiments _ -- J I ;J Wind tunnel Validation Flight test ~ Demonstratio~ ~ Industry --- Complete cost I benefit ~analysis Fig.
None of these presented an acceptable solution being either too expensive or too heavy or, in the case of electrically powered units, exceeding the spare power available on the aircraft. Finally an ejector (or jet pump) was chosen because this was affordable and sufficient bleed air power was available. However, limited design information was available and this unit was developed jointly by DLR and Nord Micro. With careful design and manufacture acceptable pump efficiency was achieved. Using a bleed air mass flow of 160 glsec at 3 bar, a suction mass flow of 100 glsec is obtained at 15-kPa pressure difference between suction surface pressure and pump outlet pressure.
35 The flight tests for the second step is envisaged to take place again in an EC programme for a flight test campaign comparable to the one described in this report. g. at research establishments in order to prepare for a larger programme to come after the HLF fin has proven its reliability for industrial use. K. for specimen and models Design based on total aircraft Part Manufacture Concepts, tests on specimen Concept rating: design to cost System Control Sophisticated but isolated solu- Aircraft system integration tions for tests Handling (Repair, Main- First ideas tenance, ...