Abstract
In the recently, it was showed that the airfoil model constructed with flat panels (based on double wedge airfoil) had the flight ability in the subsonic and transonic conditions. However there are few experimental aerodynamic data on the airfoil model constructed with flat panels in such flows. As the preliminary study, visualizations of the flow field around the double wedge airfoil model are performed with a conventional and sharp focusing schlineren method. The results show that the expansion and oblique shock waves are produced at the corner of airfoil surface on the double wedge airfoil model. Also, it is shown that this system has a capability for visualizing any cross section of transonic shock tube airfoil flow.
