By E.H. Dowell
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Additional resources for Aeroelasticity of Plates and Shells (Mechanics: Dynamical Systems)
X. 3, respectively. The incident shock wave, i, propagates up the reflecting wedge surface, towards the quiescent gas in state (0). It touches the reflecting wedge surface at the reflection point, R. The reflected shock wave, r, unlike the incident shock wave, is straight only near the reflection point. It emanates from the reflection point and terminates perpendicularly on the shock tube bottom wall. The entire reflection grows linearly with time . 2 The wave configuration of a pseudo-steady RR.
7 Definition of the flow parameter of a pseudo-steady SMR. 7. , i, r, m and s are stationary. The flow in state (0), which was originally above the triple point trajectory, encounters the incident shock wave, i, obliquely, with an angle of incidence <1>1 = 90° - (8 w + X). Upon passing through the incident shock wave, the flow is deflected towards the wedge by an angle 81' and assumes a new thermodynamic state, state (1). The reflected shock wave, r, which has an angle of incidence <1>2 with respect to the flow in state (1), deflects the flow in an opposite direction by an angle 82 to become parallel to the slipstream, s.
Consequently, they argued that transition from RR to MR takes place the very first time MR becomes theoretically possible. 17 which , as discussed earlier, corresponds also to the mechanical equilibrium criterion. Thus, the physical arguments of Hornung, Oertel & Sandeman (1979) led to two different transition lines. In steady flows it predicts transition at the same point predicted by the mechanical equilibrium criterion, and in pseudo-steady flows it predicts transition at the same point predicted by the sonic criterion.
Aeroelasticity of Plates and Shells (Mechanics: Dynamical Systems) by E.H. Dowell