抄録
We have proposed a deployable-wing airplane for Mars exploration. In the present study, wind tunnel experiments have been carried out to clarify high-speed aerodynamic characteristics of the airplane. The result shows that the wing deployment is effective to improve the lift to drag ratio (L/D) of the airplane in flow regime less than Mach number of 3.0. In transonic flow regime, a peculiar stall characteristic can be seen for the deployable wing with the sweptback angle of 45 degrees. This is considered to be caused by the vortex breakdown occurred on the wing. Due to the stall, the pitching moment coefficient (CM) shows a nonlinear characteristic. The CM tends to decrease as the sweptback angle of the deployable wing decreases, showing that the wing deployment has a great influence on the longitudinal stability of the airplane. A canard has a characteristic of transiting the angle of attack where the stall occurs to higher ranges, increasing the lift coefficient (CL) and L/D. At the same time, it has a characteristic of transiting the angle of attack where the nonlinear characteristic of the CM occurs to higher ranges. Therefore, the use of the canard enables us to obtain high CL and L/D as well as to improve the nonlinear characteristics of the CM.
