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
A review of leading edge vortex studies conducted at the University of Notre Dame is presented. The ...
Vortex flows of interest to aerodynamicists cover a wide range of scales from a fraction of an inch ...
This paper discusses further the effects of Reynolds number, angle of attack and leading edge bluntn...
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...
An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was...
An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was...
The flow behaviour over the upper surface of a blunt-edged delta wing is mainly governed by a compli...
A survey is presented of factors affecting blunt leading-edge separation for swept and semi-slender ...
Detailed pressure measurements were made on a flat semispan swept wing with a rounded leading edge a...
The Boeing Commercial Airplane Company developed an inviscid three-dimensional lifting surface metho...
This paper presents flow measurements on four delta wing configurations which are differentiated by ...
A method of predicting forces, moments, and detailed surface pressures on thin, sharp-edged wings wi...
The vortex dominated aerodynamic characteristics of a generic 65 degree cropped delta wing model wer...
A systematic analysis of incipient separation and subsequent vortex formation from moderately swept ...
A review of leading edge vortex studies conducted at the University of Notre Dame is presented. The ...
Vortex flows of interest to aerodynamicists cover a wide range of scales from a fraction of an inch ...
This paper discusses further the effects of Reynolds number, angle of attack and leading edge bluntn...
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...
An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was...
An experimental wind tunnel test of a 65 deg delta wing model with interchangeable leading edges was...
The flow behaviour over the upper surface of a blunt-edged delta wing is mainly governed by a compli...
A survey is presented of factors affecting blunt leading-edge separation for swept and semi-slender ...
Detailed pressure measurements were made on a flat semispan swept wing with a rounded leading edge a...
The Boeing Commercial Airplane Company developed an inviscid three-dimensional lifting surface metho...
This paper presents flow measurements on four delta wing configurations which are differentiated by ...
A method of predicting forces, moments, and detailed surface pressures on thin, sharp-edged wings wi...
The vortex dominated aerodynamic characteristics of a generic 65 degree cropped delta wing model wer...
A systematic analysis of incipient separation and subsequent vortex formation from moderately swept ...
A review of leading edge vortex studies conducted at the University of Notre Dame is presented. The ...
Vortex flows of interest to aerodynamicists cover a wide range of scales from a fraction of an inch ...
This paper discusses further the effects of Reynolds number, angle of attack and leading edge bluntn...