PSI - Issue 77

Koji Uenishi et al. / Procedia Structural Integrity 77 (2026) 183–189 Uenishi / Structural Integrity Procedia 00 (2026) 000–000

186

4

3

1

a

0

c < c R < c S < c P

R

Energy source

Energy source

1.25

b

c ≈ c R < c S < c P

R

R

1.25

c

S Mach front

c S < c < c P

S Mach front

0.85

d

c S < c P < c

P Mach front

P Mach front

S Mach front

S Mach front

0.45

Fig. 2. Contours of the normalized maximum in-plane shear stress τ max / A showing the wave fields for the problems in Fig. 1, at different levels of the Mach numbers M P ≡ c / c P and M S ≡ c / c S : (Left) Analytically obtained for a steady-state (left, modified after Uenishi (2025)) and (right) numerically generated for a transient motion. (a) Subsonic ( M P = 0.40, M S = 0.69), (b) subsonic Rayleigh resonance ( M P = 0.53, M S = 0.91), (c) transonic (supershear) ( M P = 0.80, M S = 1.38), and (d) supersonic ( M P = 1.60, M S = 2.76) cases (Poisson’s ratio 0.25). The normalized time c P t / r , elapsed since the start of the energy source from the bottom of the interface, is shown at the left-bottom corner of each snapshot on the right.