Adaptive Shock Control Bump Spoiler Concepts for Laminar Wings

Paper #:
  • 2017-01-2164

Published:
  • 2017-09-19
Abstract:
Drag reduction technologies in aircraft design are the key enabler for reducing emissions and for sustainable growth of commercial aviation. Laminar wing technologies promise a benefit of 3-9% of drag reduction. From the established moveable concepts and high-lift systems the most do not cope with the requirements for natural laminar flow wings. The leading edge high-lift systems have been in the focus of research activities in the last 5 years. Alternative to the conventional slat, projects addressed the development of laminar flow compatible high-lift systems like the Kruger and the Droop Nose concept. However, also hybrid laminar flow concepts are under investigation at a lot of research institutes in Europe. But not only leading edge moveables play a role in the development of new moveable concepts for laminar wings. As laminar wings are sensitive to high air speeds the control of the aerodynamic shock and buffeting becomes important. One possibility to decrease the wave drag caused by the aerodynamic shock are shock control bumps (SCBs). The objective of SCBs is the conversion of a single strong shock into several smaller and weaker λ-shocks resulting in a drag benefit when deployed correctly. Unfortunately the shock position changes with varying conditions like speed, altitude, angle of attack and others during the flight. Therefore the shock control bumps must be adaptable in position and height. However, SCBs can also help to control laminar buffeting by fixing the shock into given positions at the SCBs location. In this paper concepts for an adaptive shock control bump at the spoiler are presented. Design drivers and interdependencies are discussed. A conventional concept of an adaptive spoiler with utilizing two conventional actuators is assessed.
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