Application of linear stability theory in laminar flow designThe linear stability of fully three-dimensional supersonic boundary layers formed over swept-wing configurations is investigated using a modified version of the linear stability code COSAL. Configurations studied include a highly swept leading-edge model to be utilized for transition studies in the LARC Low-disturbance Mach 3.5 Pilot Tunnel. The model is a representation of the leading edge of a laminar flow control wing for the F-16XL aircraft. In addition, the region over a laminar flow control glove fitted on the midportion of an F-16XL wing was studied. For each configuration, estimates of the location of the onset of transition were computed using linear stability theory and the e exp N method. The effectiveness of suction in stabilizing the boundary layer over the F-16XL wing glove was also investigated.
Document ID
19920057343
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Iyer, Venkit (Vigyan, Inc. Hampton, VA, United States)
Spall, Robert (High Technology Corp. Hampton, VA, United States)