Showing papers by "Emmanuel Benard published in 1999"
TL;DR: In this article, the boundary layer transition along the attachment line of a smooth swept circular cylinder in hypersonic flow is investigated in a blowdown wind tunnel with a wide range of spanwise Mach numbers Me (3.28 to 6.78).
Abstract: The boundary layer transition along the attachment line of a smooth swept circular cylinder in hypersonic flow is investigated in a blowdown wind tunnel. A wide range of spanwise Mach numbers Me (3.28 to 6.78) is covered with the help of different models at several sweep angles (60°?Λ?80°). The transition is indirectly detected by means of heat flux measurements. The influence of the wall to stagnation temperature ratio is investigated by cooling the model with liquid nitrogen.
12 citations
28 Jun 1999
TL;DR: Boundary layer separation due to adverse pressure gradients on surfaces shock induced or otherwise has been a problem of significant interest to aircmft and turbo-machinery designers as mentioned in this paper.
Abstract: Boundary layer separation due to adverse pressure gradients on surfaces shock induced or otherwise has been a problem of significant interest to aircmft and turbo-machinery designers. Boundary layer sparation can occur in the case of aircraft (1) on wings and control surf&es due to high incidence at subsonic speeds and shock waves at transonic speeds and (2) in engine intakes and diffusers. In the case of turbo-machines separation can occur on suction side of blades of compressors and turbines. Boundary layer separation leads to an increase in drag and therefore fuel consumption and a decrease jn the aerodynamic performance. The flow uxmeadhess associated with separation (bu&t) leads to buffeting and therefore fatigue damage which limits the performance and life span of ahcraft and turbo-machines.
6 citations