EFFECT OF ANGLE OF ATTACK AND THICKNESS ON AERODYNAMIC COEFFICIENTS OF A RIGID WING OSCILLATING AT VERY LOW FREQUENCIES IN TWO-DIMENSIONAL SUPERSONIC FLOW

摘要

Analytical expressions are presented for the lift and pitching-moment coefficients of a wing of finite thickness performing a plunging motion and rotary oscillations about some fixed angle of attack at very low frequencies in two-dimensional flow.nCalculated lift and pitching-moment coefficients are presented for the entire range of angle of attack and thickness for which the flow behind the shock attached to the leading edge is everywhere supersonic, although the effect of viscous separation at the finite angles of attack restricts the validity of the results to a much smaller range of these parameters.