Recent Assessment and Analysis of Damping Derivatives for Delta Wings in Hypersonic Flow for Curved Leading Edges with Full Sine Wave

This paper presents the effect of curved leading edges on the damping derivative due to the pitch rate
for the various amplitude of the sine wave, flow deflection angle δ, pivot position, and the Mach
numbers. Results show that with the increase in the amplitude of the full sine wave (i.e., positive
amplitude) there is a progressive increase in the pitch damping derivatives from h = 0, later in the
downstream towards the trailing edge it decreases till the location of the center of pressure and vice
versa. At the location of the center of pressure, when we consider the stability derivatives in damping
for the rate of pitch q, there is an increase in the numerical values of the derivatives. This increase is
non-linear in nature and not like for position near the leading edges. The magnitude of the damping
derivatives due to the variations in the Mach numbers, flow deflection angle δ, and the amplitude of
the sine wave remained in the same range.