Experimental Investigation of Double Delta Wings with Different Angles of Attack at Subsonic Speeds

The wind tunnel experimental study has been carried out on a double delta wing of different geometrical configurations such as 80°/45°, 75°/45° and 70°/45° sweep angles given as Model I, Model II and Model III with various freestream velocities from 10 to 40 m/s with a step of 10 m/s in Hindustan Institute of Technology and Science, Chennai, Low Speed Wind tunnel (HITSLSWT). The experiment is conducted for the measurement of lift and drag forces using single component force balance. The investigation was done to look into the effects of changing the double delta wing's leading edge sweep angles. Three different models have been tested at various angles of attack ranging from 0° to +16° and 0° to −16° with 4° and four different freestream velocities based on the delta wing’s chord. It is observed that the influence of variation of leading edge sweep angles affects the performance of aerodynamic characteristics of the model. The increase in angle in attack with increased velocity gives better aerodynamic performance. This paper provides good insight into the aerodynamic force measurement of double delta wing and the low-speed performance of the models.