An experimental investigation of the transition process in boundary layers subjected to forward- or aft-facing two-dimensional step excrescences is described. The objective of the work was to characterize the variation of transition Reynolds numbers with measurable roughness and boundary layer parameters, with the specific goal of specifying new tolerance criteria for laminar flow airfoils, alongside a fundamental investigation of linear boundary layer stability mechanisms. Results from an ongoing program of increasing complexity on effects of pressure gradient on excrescence-induced transition are presented. Preliminary N-factor calculations are used to determine the effects of boundary layer stability and attempt to isolate the ef...
In modern laminar flow flight and wind tunnel research, it is important to understand the specific c...
Models for the laminar-turbulent transition zone have in recent years become increasingly important,...
The influence of unit Reynolds number (Re1=17.5E6/m to 80E6/m), Mach number (M=0.35-0.77) and incomp...
An examination of the effects of surface step excrescences on boundary layer transition was performe...
Boundary-layer surveys were made throughout the transition region along a smooth flat plate placed i...
The effect of sharp forward-facing steps on boundary-layer transition is systematically investigated...
Laminar flow has the potential to dramatically reduce fuel consumption and/or extend the range of mo...
An experimental study was undertaken to determine the effects of step excrescences on boundary layer...
The immense fuel savings and environmental benefits of reducing aircraft skin-friction drag through ...
A low-speed experiment was performed on a swept at plate model with an imposed pressure gradient to ...
Experiments were conducted in the Cryogenic Ludwieg-Tube Göttingen to study the influence of surface...
AbstractThe effect of geometric forward-facing steps on boundary layer transition was experimentally...
Boundary-layer receptivity examines the way in which external disturbances generate instability wave...
Condtions encountered in the high Mach number flow regime are show to profoundly affect the longitud...
Presented at 34th AIAA Applied Aerodynamics ConferenceThe influence of the laminar boundary-layer st...
In modern laminar flow flight and wind tunnel research, it is important to understand the specific c...
Models for the laminar-turbulent transition zone have in recent years become increasingly important,...
The influence of unit Reynolds number (Re1=17.5E6/m to 80E6/m), Mach number (M=0.35-0.77) and incomp...
An examination of the effects of surface step excrescences on boundary layer transition was performe...
Boundary-layer surveys were made throughout the transition region along a smooth flat plate placed i...
The effect of sharp forward-facing steps on boundary-layer transition is systematically investigated...
Laminar flow has the potential to dramatically reduce fuel consumption and/or extend the range of mo...
An experimental study was undertaken to determine the effects of step excrescences on boundary layer...
The immense fuel savings and environmental benefits of reducing aircraft skin-friction drag through ...
A low-speed experiment was performed on a swept at plate model with an imposed pressure gradient to ...
Experiments were conducted in the Cryogenic Ludwieg-Tube Göttingen to study the influence of surface...
AbstractThe effect of geometric forward-facing steps on boundary layer transition was experimentally...
Boundary-layer receptivity examines the way in which external disturbances generate instability wave...
Condtions encountered in the high Mach number flow regime are show to profoundly affect the longitud...
Presented at 34th AIAA Applied Aerodynamics ConferenceThe influence of the laminar boundary-layer st...
In modern laminar flow flight and wind tunnel research, it is important to understand the specific c...
Models for the laminar-turbulent transition zone have in recent years become increasingly important,...
The influence of unit Reynolds number (Re1=17.5E6/m to 80E6/m), Mach number (M=0.35-0.77) and incomp...