Abstract
For supersonic cruise aircraft, the leading-edge vortex flap (LEVF) is one of the devices which can improve the aerodynamic efficiency of delta wings at low speed. Low-speed wind tunnel tests were conducted in order to gain more understanding of the flow around the LEVF, especially to determine the condition for the optimum lift to drag ratio. The performance of an inverted vortex flap and vortex plate were measured. Associated force measurements and flow visualization tests were carried out on a 60 {degree} delta wing model. The Reynolds numbers based on the wing centreline cord were about 6 and 9*10{sup 5}. Results indicate that the maximum lift to drag ratio for any given flap deflection angle occurs when the flow smoothly comes onto the deflected vortex flap without forming a large leading-edge separation vortex on the flap surface. Use of a vortex plate was found to reduce the drag in comparison with the wing, because of a benefit due to some leading-edge suction acting on the forward facing region between the delta wing and the vortex plate. 12 refs., 16 figs.
Rinoie, K
[1]
- National Aerospace Laboratory, Tokyo (Japan)
Citation Formats
Rinoie, K.
Experimental studies of vortex flaps and vortex plates. Part 1. 0.53m span 60{degree} delta wing.
Japan: N. p.,
1992.
Web.
Rinoie, K.
Experimental studies of vortex flaps and vortex plates. Part 1. 0.53m span 60{degree} delta wing.
Japan.
Rinoie, K.
1992.
"Experimental studies of vortex flaps and vortex plates. Part 1. 0.53m span 60{degree} delta wing."
Japan.
@misc{etde_10125822,
title = {Experimental studies of vortex flaps and vortex plates. Part 1. 0.53m span 60{degree} delta wing}
author = {Rinoie, K}
abstractNote = {For supersonic cruise aircraft, the leading-edge vortex flap (LEVF) is one of the devices which can improve the aerodynamic efficiency of delta wings at low speed. Low-speed wind tunnel tests were conducted in order to gain more understanding of the flow around the LEVF, especially to determine the condition for the optimum lift to drag ratio. The performance of an inverted vortex flap and vortex plate were measured. Associated force measurements and flow visualization tests were carried out on a 60 {degree} delta wing model. The Reynolds numbers based on the wing centreline cord were about 6 and 9*10{sup 5}. Results indicate that the maximum lift to drag ratio for any given flap deflection angle occurs when the flow smoothly comes onto the deflected vortex flap without forming a large leading-edge separation vortex on the flap surface. Use of a vortex plate was found to reduce the drag in comparison with the wing, because of a benefit due to some leading-edge suction acting on the forward facing region between the delta wing and the vortex plate. 12 refs., 16 figs.}
place = {Japan}
year = {1992}
month = {Mar}
}
title = {Experimental studies of vortex flaps and vortex plates. Part 1. 0.53m span 60{degree} delta wing}
author = {Rinoie, K}
abstractNote = {For supersonic cruise aircraft, the leading-edge vortex flap (LEVF) is one of the devices which can improve the aerodynamic efficiency of delta wings at low speed. Low-speed wind tunnel tests were conducted in order to gain more understanding of the flow around the LEVF, especially to determine the condition for the optimum lift to drag ratio. The performance of an inverted vortex flap and vortex plate were measured. Associated force measurements and flow visualization tests were carried out on a 60 {degree} delta wing model. The Reynolds numbers based on the wing centreline cord were about 6 and 9*10{sup 5}. Results indicate that the maximum lift to drag ratio for any given flap deflection angle occurs when the flow smoothly comes onto the deflected vortex flap without forming a large leading-edge separation vortex on the flap surface. Use of a vortex plate was found to reduce the drag in comparison with the wing, because of a benefit due to some leading-edge suction acting on the forward facing region between the delta wing and the vortex plate. 12 refs., 16 figs.}
place = {Japan}
year = {1992}
month = {Mar}
}