The Numerical Investigation of The Aerodynamics of a Lambda Wing In Static Ground Effect

The In this research, aerodynamics forces and lambda wing flow physics with a sharp leading edge and leading edge sweep angles of 54.9° and 29.5° have been investigated in the ground effect region numerical method. At Mach number 0.2, angle of attack from 0° through 8°, with clearance free stream through 0.05 is varying. The equations is solved based on the finite volume method. Two equation k- SST model is used for turbulence modeling. The drag, lift, nose up moment, aerodynamics efficiency, parasitic drag increase with decreasing flight height, and decrease the induced drag. The coefficients variations percentage relative to free stream increases with height decreasing and angle of attack, and most variation percentage are at clearance from 0.3 to 0.05.The study flow physics at angle of attack 8° is exhibited with the flight height decreasing, the flow between the ground and the windward side is blocked to decrease dynamic pressure and increase static pressure. Also, suction on the leeward side increase and the strengthened primary vortex. With the flight height decreasing, wing kink location vortex is weakened and vortex breakdown is transferred to the upstream flow.