Plasma Control Of Vortex Flow On Delta-Wing At High Angles Of Attack

Nomenclature AR = wing aspect ratio b = wing thickness Cp = pressure coefficient, (p-p0)/q+1 c = wing root chord length Cxa = drag coefficient Cya = lift coefficient Cza = side force coefficient K = lift-drag ratio, mxa = roll moment coefficient mza = pitching moment coefficients p = static pressure on the model surface Tu = free-stream turbulence level, % of U∞ U∞ = mean free-stream velocity q = dynamic pressure x = vortex breakdown position along the wing chord z = transversal direction along the wing span α = angle of attack χ = delta-wing leading edge sweep angle