Add to ORKGA review is presented of the initial experimental results and analysis that formed the basis the Vortex Flow Experiment 2 (VFE-2). The focus of this work was to distinguish the basic effects of Reynolds number, Mach number, angle of attack, and leading edge bluntness on separation-induced leading-edge vortex flows that are common to slender wings. Primary analysis is focused on detailed static surface pressure distributions, and the results demonstrate significant effects regarding the onset and progression of leading-edge vortex separation
In order to clarify the mechanism by which aerodynamic noise is generated from separated flow around...
A 65 o delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic chord...
In order to clarify the mechanism by which aerodynamic noise is generated from separated flow around...
A review is presented of the initial experimental results and analysis that formed the basis the Vor...
A review is presented of the initial experimental results and analysis that formed the basis the Vor...
The flow behaviour over the upper surface of a blunt-edged delta wing is mainly governed by a compli...
This paper discusses further the effects of Reynolds number, angle of attack and leading edge bluntn...
A review of leading edge vortex studies conducted at the University of Notre Dame is presented. The ...
The main objective of this project is to investigate the flow characteristics of the VFE- 2 blunt ed...
Available experimental data on a 65xB0; swept back cropped delta wing with rounded leading edges hav...
A survey is presented of factors affecting blunt leading-edge separation for swept and semi-slender ...
A 65 deg delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic cho...
When a thin delta wing with high leading-edge sweep is placed at incidence in a stream, the fluid se...
In this paper the present knowledge on the vortex formation on slender delta wings is summarized. Th...
Leading edge vortex (LEV) formation, which is initiated by separation at the leading edge, depends o...
In order to clarify the mechanism by which aerodynamic noise is generated from separated flow around...
A 65 o delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic chord...
In order to clarify the mechanism by which aerodynamic noise is generated from separated flow around...
A review is presented of the initial experimental results and analysis that formed the basis the Vor...
A review is presented of the initial experimental results and analysis that formed the basis the Vor...
The flow behaviour over the upper surface of a blunt-edged delta wing is mainly governed by a compli...
This paper discusses further the effects of Reynolds number, angle of attack and leading edge bluntn...
A review of leading edge vortex studies conducted at the University of Notre Dame is presented. The ...
The main objective of this project is to investigate the flow characteristics of the VFE- 2 blunt ed...
Available experimental data on a 65xB0; swept back cropped delta wing with rounded leading edges hav...
A survey is presented of factors affecting blunt leading-edge separation for swept and semi-slender ...
A 65 deg delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic cho...
When a thin delta wing with high leading-edge sweep is placed at incidence in a stream, the fluid se...
In this paper the present knowledge on the vortex formation on slender delta wings is summarized. Th...
Leading edge vortex (LEV) formation, which is initiated by separation at the leading edge, depends o...
In order to clarify the mechanism by which aerodynamic noise is generated from separated flow around...
A 65 o delta wing has been tested in the National Transonic Facility (NTF) at mean aerodynamic chord...
In order to clarify the mechanism by which aerodynamic noise is generated from separated flow around...