Wave drag characteristics of a low-drag supersonic formation flying concept was investigated using Euler simulations. The dependence of wave drag to the relative position of the aircraft was analyzed to evaluate the effectiveness of supersonic formation flying concept. Euler simulations was carried out using TAS-flow, an unstructured Euler/Navier-Stokes solver, and the computational mesh was generated using EdgeEditor and TU TetraGrid. The angle of attack of the aircraft was fixed at α = 3.25 ° and the aerodynamic characteristics was evaluated by comparing the changes in the CL and CD of the aircraft. It was observed that the grid between the leading and trailing aircraft was dense due to presence of dense surface mesh between two surfaces. Result shows that the reduction in Cp near the leading edge of the aircraft due to the impinging of the expansion fan extending from the leading aircraft cause decrease in the drag of the aircraft.
ASJC Scopus subject areas
- Aerospace Engineering