Novel High-Performance Grid Fins for Missile Control at High Speeds: Preliminary Numerical and Experimental Investigations

摘要

This work investigates locally swept grid fins (lattice wings) in terms of their performance over conventional lattice wings at high speeds. The study includes numerical simulations of the supersonic flow around conventional and locally swept planar and lattice wings of infinite span as well as direct force measurements at corresponding realistic finite span models in the Ludwieg Tube Facility at DLR (RWG). The investigations were performed at free-stream Mach numbers from 2 to 6 for angles of attack varying from 0 to 10 degrees. The performance of the lattice wings was assessed on the basis of zero-lift drag and lift-to-drag ratio, both 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 conventional not-swept configurations. Compared to conventional lattice wings, the maximum benefit of zero-lift total drag for these locally swept lattice wings is approximately 30%-40%.