Add to ORKGThe viscous-inviscid interactions which perturb the flow around the wing leading edge are discussed. The flow field perturbation results when the fuselage-generated shock wave interacts with the wing-generated shock wave. Three types of shock interference patterns are possible for the wing leading edge of the orbiter
The interaction region generated by separation of two supersonic streams past a finite-thickness bas...
A review is given of computations for a series of nominally 2-D laminar viscous-inviscid interaction...
The shock interaction originating from a hypersonic laminar flow over a double-wedge can lead to dif...
An experimental investigation of supersonic flow past double-wedge configurations was conducted. Ove...
Numerical codes were developed to calculate the two dimensional flow field which results when supers...
The convective heat transfer distribution for space shuttle configurations is discussed. The viscous...
In this paper, the shock pattern oscillations induced by shock/shock interactions over double-wedge ...
An experimental investigation on shock-shock interactions has been conducted with the aim of studyin...
A change in flow pattern that was observed as the free-stream Mach number was increased in the vicin...
An experimental investigation was conducted on space shuttle type, body-wing configurations. The pur...
An analytical method is suggested for the study of the viscid inviscid interaction associated with i...
Composite photographs of the surface flow and shadowgraphs of the shock wave pattern are presented t...
The development of the flow pattern that arises during the interaction of a shock wave with a wedge ...
AbstractShock wave diffraction occurs when a normal travelling wave passes through a sudden area exp...
This paper examines the Shock/Shock Interactions (SSI) between the body and wing of aircraft in supe...
The interaction region generated by separation of two supersonic streams past a finite-thickness bas...
A review is given of computations for a series of nominally 2-D laminar viscous-inviscid interaction...
The shock interaction originating from a hypersonic laminar flow over a double-wedge can lead to dif...
An experimental investigation of supersonic flow past double-wedge configurations was conducted. Ove...
Numerical codes were developed to calculate the two dimensional flow field which results when supers...
The convective heat transfer distribution for space shuttle configurations is discussed. The viscous...
In this paper, the shock pattern oscillations induced by shock/shock interactions over double-wedge ...
An experimental investigation on shock-shock interactions has been conducted with the aim of studyin...
A change in flow pattern that was observed as the free-stream Mach number was increased in the vicin...
An experimental investigation was conducted on space shuttle type, body-wing configurations. The pur...
An analytical method is suggested for the study of the viscid inviscid interaction associated with i...
Composite photographs of the surface flow and shadowgraphs of the shock wave pattern are presented t...
The development of the flow pattern that arises during the interaction of a shock wave with a wedge ...
AbstractShock wave diffraction occurs when a normal travelling wave passes through a sudden area exp...
This paper examines the Shock/Shock Interactions (SSI) between the body and wing of aircraft in supe...
The interaction region generated by separation of two supersonic streams past a finite-thickness bas...
A review is given of computations for a series of nominally 2-D laminar viscous-inviscid interaction...
The shock interaction originating from a hypersonic laminar flow over a double-wedge can lead to dif...