Design of Experiments for Wind Tunnel Testing of 53° Sweep Lambda UCAV Configuration

The steady-state and dynamic design of experiments for 53° sweep lambda wing-unmanned combat aerial vehicles (UCAV) configuration is discussed in detail. The design of the experiments was done in the Universiti Teknologi Malaysia Low-Speed wind Tunnel (UTM-LST) and contains force and moments balance and surface flow visualization with the pitch angle and yaw angle variation for the steady-state experiments and the dynamic oscillatory rig facility with 1 degree of freedom oscillating mechanism was fixed to rotate in yawing axis to focus on the sensitivity for the yaw angle for the dynamic investigations. The steady-state experiments will be capable to give the steady-state aerodynamic derivatives, while the dynamic testing will provide the trainset aerodynamic derivatives. The steady-state and the dynamic measurements will help in studying the unsteadiness and the uncertainties of the flow over the wing configuration.