Shock Control Bumps on Transonic Transport Aircraft
Published on 1. June 2014
Book
Paperback/Softback
183 pages
978-3-8439-1594-6 (ISBN)
Description
Current long range aircraft travel in the transonic speed regime, where compressibility effects of the air in the form of shocks limit the aircraft performance. One way to increase the aircraft's efficiency during the transonic cruise could be
to apply means of shock control in order to reduce the drag effect of the shock. Extensive research over the last two decades has shown that one potential candidate to achieve this is the so-called shock control bump.
The present work closes the gap between academic research and a potential industrial application by developing a set of general design guidelines for non-adaptive shock control bumps that allow to rapidly achieve designs of a good standard. This methodology is a first step towards an industrialisation of the concept and can be useful to realise a future fully integrated wing design in the presence of shock control bumps.
The numerical simulations of shock control bumps in this work are supported by wind tunnel measurements. These experimental results are used to both validate the relatively new concept of three-dimensional shock control bumps on airfoils and wings as well as the numerical methods applied.
The aim of this work is to bring the previous academic research on shock control bumps closer to an industrial implementation. It sets out to show that shock control bumps are a viable concept for drag reduction on transonic
transport aircraft and to enable the efficient incorporation of this concept into an integrated design process.
to apply means of shock control in order to reduce the drag effect of the shock. Extensive research over the last two decades has shown that one potential candidate to achieve this is the so-called shock control bump.
The present work closes the gap between academic research and a potential industrial application by developing a set of general design guidelines for non-adaptive shock control bumps that allow to rapidly achieve designs of a good standard. This methodology is a first step towards an industrialisation of the concept and can be useful to realise a future fully integrated wing design in the presence of shock control bumps.
The numerical simulations of shock control bumps in this work are supported by wind tunnel measurements. These experimental results are used to both validate the relatively new concept of three-dimensional shock control bumps on airfoils and wings as well as the numerical methods applied.
The aim of this work is to bring the previous academic research on shock control bumps closer to an industrial implementation. It sets out to show that shock control bumps are a viable concept for drag reduction on transonic
transport aircraft and to enable the efficient incorporation of this concept into an integrated design process.