Novel Locally Swept Lattice Wings for Missile Control at High Speeds

Abstract

The aerodynamic performance of novel locally swept lattice wings was investigated using 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, which 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, both the major parameters in wing design. The numerical and experimental results show that the novel design of the lattice wings has distinct advantages in comparison to the conventional non-swept configurations. For example, compared to conventional lattice wings, the investigated locally swept lattice wings achieved a reduction in the zero-lift total drag of up to 30% – 40 %.