Improvement of Aerodynamic Characteristics of Basic Configuration for Winged Vehicles with Lateral Blowing in Subsonic Flow

Abstract

An experimental study on the improvement of aerodynamic characteristics of basic configuration for winged vehicles with lateral blowing in subsonic flow has been conducted. Wing planform is 75^º/45^º double delta wing whose cross section is modified NACA0010. Lateral blowing is realized by injecting a pair of sonic jets parallel to the trailing edge of the wing. The experiments have been conducted in the transonic wind tunnel of JAXA (Japan Aerospace Exploration Agency) under the testing condition of free-stream Mach number M_∞=0.3, Reynolds number Re=2.14×10⁶, angle of attack α=-15–40^º and jet momentum coefficient C_μ=0.0166,0.0295 and 0.0398. The results show that the lift coefficient C_L and lift-to-drag ratio L/D are increased by lateral blowing over the wide range of angle of attack. The results suggest that lateral blowing can be useful for the improvement of aerodynamic characteristics of basic configuration for winged vehicles in subsonic flow.