An experimental study of a 65-degree delta wing with different pitching rates

Modern fighter aircraft require high-lift and low-drag forces to maintain their manoeuverability against advances in guided missiles. This paper presents an investigation of the behaviour of a 65-degree swept wing with sharp leading edge under static and dynamic conditions, for low- and high-angle of attack, with more emphasis around the stalling region. The study involves flow visualization and force balance measurement in a wind tunnel. Comparisons of α_stall, C_L, C_Lα, C_Lmax, C_D, C_L/C_D, (C_L / C_D)_max, C_m, and C_mα, are reported for static and dynamic cases. The results show that fast pitch up and slow pitch down motions are recommended for aircraft manoeuvre at high angles of attack to delay stalling and to maintain high-lift and low-drag forces.