Add to ORKGA six component force balance was used to obtain the CL for a reverse delta wing and a delta wing for comparison purposes. A simulation of the streamlines, velocity vectors and surface pressure contours was carried out using CFD software to show the characteristics of the flow over a reverse delta wing
The developments of highly maneuverable aircraft have prompted the extensive studies of the flow pas...
The vortical flow over swept wings with several leading edge separations bears a number of challeng...
The overall goal of the research presented in this thesis is to extend the physical understanding of...
A six component force balance was used to obtain the CL for a reverse delta wing and a delta wing f...
Particle image velocimetry was used in a low-speed wind tunnel to investigate the vortex structures ...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
Particle Image Velocimetry was used in a low speed wind tunnel to investigate the vortex structures ...
Particle Image Velocimetry was used in a low speed wind tunnel to investigate the vortex structures ...
The objective of this paper was to model the stability and control derivatives using Computational F...
The developments of highly maneuverable aircraft have prompted the extensive studies of the flow pas...
The developments of highly maneuverable aircraft have prompted the extensive studies of the flow pas...
The vortical flow over swept wings with several leading edge separations bears a number of challeng...
The overall goal of the research presented in this thesis is to extend the physical understanding of...
A six component force balance was used to obtain the CL for a reverse delta wing and a delta wing f...
Particle image velocimetry was used in a low-speed wind tunnel to investigate the vortex structures ...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
The unsteady flow past a reverse delta wing is simulated numerically to characterize the structure o...
Particle Image Velocimetry was used in a low speed wind tunnel to investigate the vortex structures ...
Particle Image Velocimetry was used in a low speed wind tunnel to investigate the vortex structures ...
The objective of this paper was to model the stability and control derivatives using Computational F...
The developments of highly maneuverable aircraft have prompted the extensive studies of the flow pas...
The developments of highly maneuverable aircraft have prompted the extensive studies of the flow pas...
The vortical flow over swept wings with several leading edge separations bears a number of challeng...
The overall goal of the research presented in this thesis is to extend the physical understanding of...