By Gabi Ben-Dor
This booklet is a accomplished state-of-the-knowledge summation of concern wave mirrored image phenomena from a phenomenological perspective. It contains a thorough advent to indirect surprise wave reflections, facing either standard and Mach varieties. It additionally covers intimately the corresponding - and three-shock theories. The publication strikes directly to describe mirrored image phenomena in numerous stream varieties, in addition to delivering the solution of the Neumann paradox.
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Additional info for Shock Wave Reflection Phenomena
8 The wave configuration of a pseudo-steady TMR. terminating on the slipstream. The existence of this compression wave was verified experimentally by Ben-Dor & Glass (1978) who evaluated finite fringe interferograms using a computerized technique [for details see Ben-Dor & Whitten (1979)] in order to obtain density contours in the flow field. 8. Note that an SMR with a curled slipstream has never been observed, hence it is quite possible that, when the compression wave is strong enough, it imposes high enough pressures to force the slipstream to curl forward, as shown in figure 2.
13), and replacing 82 by 8 28• It is again worthwhile noting that the sonic criterion results in transition conditions which are very close to those resulting from the detachment criterion. In many cases the difference in the value of the reflecting wedge angle is only a fraction of a degree. For this reason it is almost impossible to distinguish experimentally between the sonic and detachment criteria. It is important to note, however, that Lock & Dewey (1989) have developed an ingenious experimental set-up by which they were able to experimentally distinguish between the "sonic" and the "detachment" criteria.
16c, respectively. 27) should be modified. 27) gives the appropriate condition across the slipstream. 28) since the deflection angles of the flow passing through the incident and reflected shock waves are in the same direction. 28) can be used since for this case, the reflected shock wave is normal to the oncoming flow, and hence 82 = O. , <1>2 = 90°. Thus, the three-shock theory can be significantly simplified for this case. 16b, which based on the foregoing theoretical arguments is possible, does not materialize in reality.