A concept for nozzle design which incorporates slow expansion rates and a radial flow region is developed for use on a hypersonic (Mach 6) nozzle. It is shown that the boundary-layer suction slot upstream of the nozzle throat is necessary to remove upstream turbulent boundary layers and to initialize a new laminar boundary layer on the downstream nozzle wall. In effect, the laminar boundary-layer flow can be extended more effectively farther downstream by a slow expansion contour based on the present design concept than by a rapid expansion contour used in previous pilot quiet nozzles.
Goertler instability and hypersonic quiet nozzle design
1991-06-01
Conference paper
No indication
English
Goertler instability and hypersonic quiet nozzle design
NTRS | 1993
|Goertler instability and hypersonic quiet nozzle design
AIAA | 1993
|Goertler instability and hypersonic quiet nozzle design
AIAA | 1991
|Görtler Instability and Hypersonic Quiet Nozzle Design
Online Contents | 1993
|