Passive Transonic Shock Control on Bump Flow for Wing Buffet Suppression

Since modern transport aircraft cruise at transonic speeds, shock buffet alleviation is one indispensable challenge that civil research needs to be addressed. Indeed, in the flow regime shock-induced separation and compromise flight envelope of an aircraft, therefore its operational safety structural integrity. One possible solution control delay boundary layer separation. The aim this work was study whether sub-boundary scale period roughness, which locally increases displacement thickness, can act as a virtual bump, with bifurcating foot wave reduce shock’s adverse effect on same way solid bumps are known act. This passive approach then enhance margin, consequently extending safe envelope. An experimental investigation performed, applying technique wind tunnel wall bump model simulated over upper surface aerofoil. results, terms pressure distribution corresponding shadowgraph visualisation, showed such periodic roughness can, indeed, bifurcate separations, depending orientation periodicity. A produced using roughness.