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Fig. 19 | Advances in Aerodynamics

Fig. 19

From: Wall pressure beneath a transitional hypersonic boundary layer over an inclined straight circular cone

Fig. 19

The evolution of u2,rms (a, I-III) and prms (b, I-III) in the wall-normal planes at x=200 mm (I), 230 mm (II) and 260 mm (III) during the breakdown of stationary crossflow vortices in a high-speed swept wing boundary layer (Chen et al.: Stationary cross-flow breakdown in a high-speed swept-wing boundary layer, submitted). The dashed lines represent the temporal mean of the vortex-axial oriented velocity u2

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