Compressible linear boundary-layer stability analyses of two representative axisymmetric fuselage geometries indicate that a favorable effect will be exerted on the characteristics of a fuselage's axisymmetric boundary layer by compressibility. A freestream Mach number increase from 0.6 to 0.8 significantly reduces TS wave growth rates in the laminar boundary layer of the fuselages analyzed. The generally destabilizing effect of increasing length Re number on boundary layer stability can be overpowered by the favorable effects of compressibility on the fluid.
Effects of compressibility on design of subsonic fuselages for natural laminar flow
Journal of Aircraft ; 25
1988-09-01
Miscellaneous
No indication
English
Design of Natural Laminar Flow Fuselages
British Library Online Contents | 1994
|Design of Natural Laminar Flow Fuselages
British Library Conference Proceedings | 1994
|