Effect of Canard to the Aerodynamic Characteristics of Blended Wing Body Airplane

This paper describes a series of ongoing wind tunnel experiments of Blended Wing Body equipped with canard as longitudinal control surface. The canard has a rectangular shape with fixed aspect ratio and planform area. All tests were conducted in the subsonic wind tunnel at the Universiti Teknologi MARA, at Mach number of 0.1. Angles of attack, alpha were varied from -16 degrees to 50 degrees. The lift curve slope, C-L alpha shows that the lift coefficient does not change much with different canard setting angles. As expected, the lift coefficient increases with increasing angles of attack at any canard setting angle. In general, the moment coefficient increases as the canard setting angle is increased. The visualization using mini tufts were performed to observe airflow at the upper surface of the canard.