Stability and Control Characteristic Analysis of Tailless Delta Wing Aircraft through Pilot Wind-Tunnel Test

This paper contains the pilot wind tunnel test result of a scaled model to figure out the aerodynamic characteristics in the initial design phase. The initial model is designed as tailless delta wing type. Many papers dealt with the characteristics of this kind of aircraft and the wind tunnel test result performed coincides with these results. Basically, this type of aircraft does not have a horizontal tail and vertical tail, it shows unstability in either lateral/directional axis and longitudinal axis as well. It also shows abrupt increase in pitching moment over a certain angle of attack, which means the Flight Control Law would be designed very carefully to fly the aircraft safely and effectively.