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various span locations. For simplicity of 2-D rendition, 9 points in the oscillatory cycle are
chosen for display of the Cp, as shown in Figure 6-23.
Figure 6-24 and Figure 6-25 illustrate a sequence of images visualizing the flow computed
for the sinusoidal pitching-motion depicting instantaneous Mach = 1 boundary and vorticity
magnitude iso-surfaces, respectively, colored by pressure. The AOA is shown as a function of
time in the lower right-hand corner in each set of images. The left set of images, A) and B),
display the 1Hz ±2° Grid0 case results, and the 8Hz ±0.5° Grid9 case results are presented in C)
and D). Each figure’s perspective is from the top of the left wing.
It is seen from Figure 6-24 that the Mach=1 iso-surface is maximum in size at the top of
the oscillation. Throughout the oscillation, the aft extent of the upper-surface Mach=1 iso-surface
maintains a mostly constant position on the aft portion of the wing, parallel to the TE. At the
peak of the oscillatory cycle, there is a notable break-up of the Mach=1 iso-surface along the
wingtip in the 1Hz ±2° case. This result is due to the wingtip vortical structure seen in Figure 6-
25. Evidence of the vortices coming off of the strake is noticed in the cave-like feature on the
inboard portion of the wing. Upon animation of the 1Hz ±2° case, it is revealed that as the
aircraft pitches nose-down, the Mach=1 iso-surface completely wraps around the wingtip at the
LE to the bottom surface of the wing and spreads along the LE. A Mach=1 boundary iso-surface
also develops on the lower fuselage of the aircraft as the aircraft pitches nose-down and joins the
Mach=1 iso-surface that wraps around the wing. In contrast, the Mach=1 iso-surface is not as
large for the 8Hz ±0.5° case, does not spread all the way along the LE to the root of the wing,
and does not develop on the fuselage.
Figure 6-25 also displays evidence of the strong wing-tip vortices manifesting at the peak
of the sinusoidal cycle. Upon animation of both the upper and lower wing surfaces, the strake
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