Stoßkontrollbeulen zur Verzögerung des transsonischen Buffets am hybriden Laminarflügel

This work describes parameter studies of shock control bumps focused on delay of buffet onset. A two-dimensional wing section simulation setup was derived, consistently with the 3D flow about the mid-wingof a swept wing aircraft equipped with a hybrid laminar flow controlsuction system. Two bump shapes respecting constraints of the existing spoiler were defined and analyzed for their ability to delay the onset oftransonic buffet. Both types of geometry were found to be able to delay the occurrence of buffet at the given cruise conditions, with both cases requiring bumps whose crest is positioned far downstream. Both smooth curvature devices and structurally realizable bumps showed potential benefits, moving buffet onset to higher lift coefficients cL