Flow studies of a forward swept wing fitted with active flow control

The study of synthetic jet is considered an important fluid mechanical flow control device. This device can be used in many different applications to enhance or inhibit the desired flow properties or flow performance. The test model consisted of a forward swept wing scaled from the Grumman X-29 experimental aircraft. The wing was fitted with multiple surface pressure taps to determine the flow profiles over the wing top and bottom surfaces. A polymer composite material, 'Renshape' was used to generate the part in less time than that would take to produce an aluminium version or other metallic version. It was investigated for flexural rigidity to maintain the specified geometry. The wing also contained the tappings for the injection of synthetic jet ports at the specified locations. The method of injection was remote from the wing using plastic tubing to connect the synthetic jet actuator to the wing injection ports. A reciprocating piston device was used to generate synthetic jet characteristic oscillatory flow. The shape of the synthetic jet orifices, were circular and flush with the wing surface. The synthetic jet was introduced at different locations to delay separation and/or cause re-attachment of separated flow. The results obtained suggested that asymmetrical localised synthetic jet improved the aerodynamic performance on a symmetrical wing namely the NACA-0012 airfoil and that the optimal synthetic jet angle of 23° appeared to be optimum to reduce flow separation at 15° AOA.