Browsing by Author "Rinoie, K."
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Item Open Access Experimental studies of vortex flaps and vortex plates(1991) Rinoie, K.Low-speed wind tunnel tests have been made to investigate the flow around a leading-edge vortex flap at the maximum L/D condition. Tests were also made to measure the performance of the inverted vortex flap and the vortex plate. The force measurements and flow visualization tests were conducted on a 60deg delta wing model. Results indicate that the lift to drag ratio is a maximum for any given flap deflection angle when the flow comes smoothly onto the deflected vortex flap without forming a large leading-edge separation vortex on the flap surface. The benefit of the vortex plate is seen in the drag results which are smaller than those for the datum wing. This benefit is due to some leading-edge suction acting on the forward facing region between the delta wing and the vortex plate.Item Open Access Low speed aerodynamic characteristics of 60 degrees rounded leading-edge delta wing with vortex flaps(1996) Rinoie, K.Low speed wind tunnel measurements have been made on a 1.15m span 60º delta wing with rounded leading-edge vortex flaps. the purpose of the measurements was to assess the benefits of the measurements was to assess the benefits of the rounded leading-edge vortex flaps on the lift/drag ratio. The force and surface pressure measurements were made at a Reynolds number based on the centreline chord of 2x106. The increase in the radius of the rounded leading-edge reduces the drag significantly both with and without flap deflection except in the minimum drag region. Deflecting the rounded leading-edge vortex flap improves the lift/drag ratio compared with the sharp edged vortex flap at relatively higher lift coefficients. The greatest percentage improvement in the lift/drag ratio compared with the sharp edged flat delta wing is more than 50% at a lift coefficient of 0.5 for the rounded edge delta wing with flap deflected.Item Open Access Low speed aerodynamic characteristics of 60 degrees rounded leading-edge delta wing with vortex flaps(1996) Rinoie, K.Low speed wind tunnel studies have been conducted to investigate the effect of vortex flaps with a rounded leading-edge on delta wing performance. Measurements were done using the 60º delta wing at a Reynolds number based on the centre line chord 8x10(5). Results indicated that the rounded leading-edge delta wing with 30º vortex flap deflection improves the lift/drag ratio at lift coefficients higher than 0.4, when compared with the sharp leading-edge flat delta wing. The effect of a trailing-edge flap with vortex flaps was also investigated.