Reynolds Number And The Leading Edge Of A Blunt Delta Wing Aerodynamic Performance

Aircraft performances are becoming more and more important in modern military affairs. Delta wings and double-delta wings are adopted in many fighters for more agility and maneuverability. At moderated angles of attack, separation occurs at the leading edge of delta wings, and there will reside a pair of vortices above the upper wing surfaces. These vortices will generate additional lift called "vortex lift", which will benefit aircraft performance.The author here studied the effects of both leading edge bluntness and Reynolds number to aerodynamic characteristics of delta wings, through numerical simulation. The contents include:1. High quality viscosity grids are generated using algebraic method and smoothed by solving elliptic equations, then applied in the following research.2. The separation flow at delta wing leading edge is simulated using N-S equations, by selecting appropriate discretization methodology and turbulence models.3. The effects of leading edge bluntness on leading edge separating vortices of delta wings and separating locations and separating angles.4. The Reynolds effects on leading edge separating vortices of delta wings and separating locations and separating angles.The research show that, leading edge bluntness and Reynolds effects will suppress and delay leading edge separation.