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

Abstract

The object of this work is the investigation of new locally swept grid fins (lattice wings) regarding its potential of the performance improvement at high speeds. Detailed examinations include numerical simulations of the supersonic flow around the 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 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 not-swept 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%.