Unlike the reflection process in pseudo-steady flows, where it is coupled with an additional process, namely, the flow deflection process (see section 2.6.1), in steady flows the reflection process is independent.
Unlike the analysis of the reflection process in pseudo-steady flows, where there is a need to analytically predict the first triple point trajectory angle, χ, in order to transform the results from the (Ms, \(\theta _w^c\))-plane to the more physically meaningful and more applicable (Ms, θw)-plane, in steady flows the results are presented in the (M0,ø1)-plane. The presentation of the results in this plane can be done by solving equations (1.14) to (1.27) without the need for an additional expression for χ [equation (2.33)] as discussed in section 2.2.1.
Of the ten different shock wave reflection configurations mentioned in section 1.1 only two, namely, RR and SMR, are possible in steady flows.
KeywordsShock Wave Triple Point Incident Shock Incident Shock Wave Reflection Point
List of Symbols
length of the Mach stem
length of the reflecting wedge
flow Mach number in state (i)
incident shock wave Mach number
static pressure in state (i)
flow velocity in state (i)
specific heat capacities ratio
maximum deflection angle for a flow having Mach number M through an oblique shock wave
reflecting wedge angle
complementary wedge angle
Mach angle of the flow having a Mach number Mi
flow density in state (i)
angle of incidence between the flow and the oblique shock wave across which the flow enters state (i)
limiting angle of incidence
flow state ahead of the incident shock wave, i.
flow state behind the incident shock wave, i.
flow state behind the reflected shock wave, r.
flow state behind the Mach stem, m.
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