in this study, aerodynamic characteristics of a circular cylinder in an axial flow have been investigated numerically and experimentally. the model has been considered as a cylinder with truncated nose and fineness ratio of 3 (length to diameter ratio of 3). the investigation involves a series of wind tunnel measurements, flow visualization, and numerical simulation. we used different mach numb...

This paper describes experimental observations of various phenomena characteristic of dynamic intersonic decohesion of bimaterial interfaces[ Two separate but complementary optical methods are used in con! junction with high!speed photography to explore the nature of the large!scale contact and mach wave formation at the vicinity of running cracks in two di}erent bimaterial systems[ Theoretical...

The purpose of this paper is to synthesize the most important results of the thesis work of Meredith (1990) concerning radiation from seismic sources in boreholes. Previous studies of radiation from sources in boreholes have been far-field studies and have neglected the explicit contribution of the borehole. In general, this is fine for P-wave radiation and for S-wave radiation into high veloci...

A generalized hydrodynamic theory of shock wave structures is presented for rigid diatomic gases. The theory yields shock solutions for all Mach numbers. The accuracy of the theory is examined for nitrogen gas as an example. Excellent agreement with experiment is obtained for the inverse shock widths for the entire range of Mach number studied by experiment. The comparison made shows that we ar...

This study concerns the hypersonic flow over blunt bodies in two specific cases. The first is the case when the Mach number is infinite and the ratio of the specific heats approaches one. This is sometimes referred to as the ‘Newtonian limit’. The second is the case of infinite Mach number and very large streamwise distance from the blunt nose with a strong shock wave, or the ‘blast wave limit ...

SUMMARY An asymptotic analysis of the compressible Euler equations in the limit of vanishing Mach numbers is used as a guideline for the development of a low Mach number extension of an explicit higher order shock capturing scheme. For moderate and large Mach numbers the underlying explicit compressible ow solver is active without modiication. For low Mach numbers, the scheme employs an operato...

In developing the next generation supersonic transport airplane, two major challenges must be resolved. The fuel efficiency must be significantly improved, and the sonic boom propagating to the ground must be dramatically reduced. Both of these objectives can be achieved by reducing the shockwaves formed in supersonic flight. The Busemann biplane is famous for using favorable shockwave interact...

The purpose of this experiment was to observe the wave-particle duality of photons by demonstrating that single photons can and do interfere with themselves. This was accomplished through the use of a Mach-Zehnder interferometer and a Young double slit apparatus. The EMCCD camera used for both experiments can detect single photons to some degree, thus demonstrating the particle nature of photon...

In engineering practice, when the flight Mach number is beyond the design Mach number, or the actual flight attack exceeds rated value, the waves generated by forebody would interact with lip boundary layer, which may result in inlet unstart. In figure 1, a sizable wave pattern occurs at the lip leading edge, which includes various basic physical appearances such as viscous flow, separation, an...