The performance of transport aircraft can be considerably improved if the process by which the wing boundary layer becomes turbulent can be controlled and extensive areas of laminar flow maintained. In order to design laminar flow control systems, it is necessary to be able to predict the movement of the transition location in response to changes in control variables, e.g., surface suction. At present, the technique which is available to industry requires excessively long computational time – so long that it is not suitable for use in the "design process." Therefore, there is a clear need to produce a system which delivers results in near realtime, i.e., in seconds rather than hours. This article details how parallel computing techniques on a KSR-1 produce these performance improvements.
Corrigendum to “Review of hybrid laminar flow control systems” [Prog. Aero. Sci. 93(2017), 24–52]
