Development of an Aerodynamic Model for a Delta-Wing Equivalent Model Ⅱ (EQ-Ⅱ) Aircraft

摘要

An aerodynamic model is developed for an aircraft to represent the performance and maneuvering capabilities of a delta-wing subsonic long range tailless aircraft. This aerodynamic model is implemented into an integrated simulation environment for the purpose of aerial refueling and formation flight simulation. The aerodynamic coefficient data of the Equivalent Model Ⅱ (EQ-Ⅱ) aircraft and damping derivative data were estimated using vortex lattice methods with empirical corrections for the EQ-Ⅱ configuration. Control surface effectiveness of the EQ-Ⅱ which utilizes clamshells and elevons for pitch, roll, and yaw control, was also estimated using the same methods. This paper presents the aerodynamic force and moment coefficients in the form of polynomial expressions fitted into these data points.