Wave Drag Reduction Approach for Lattice Wings at High-Speeds

Abstract

The investigations of the aerodynamic performance of new locally swept lattice wings include numerical simulations as well as wind tunnel measurements. The investigations were performed at free-stream Mach numbers from 2 to 6 for angles of attack varied from 0 to 10 degrees. The performance of the lattice wings was assessed on the basis of the zero-lift drag and lift-to-drag ratio. The numerical and experimental results show that the novel design of the lattice wings has distinct advantages in comparison to the conventional unswept configurations. Compared to conventional lattice wings the maximum benefit e.g. of the zero-lift total drag for the investigated locally swept lattice wings is of the order of 30% - 40%.