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In aerodynamics, the normal shock tables are a series of tabulated data listing the various properties before and after the occurrence of a normal shock wave. [1] With a given upstream Mach number , the post-shock Mach number can be calculated along with the pressure , density , temperature , and stagnation pressure ratios.
Figure 1 shows a typical plot of the rate of crack growth as a function of the alternating stress intensity or crack tip driving force plotted on log scales. The crack growth rate behaviour with respect to the alternating stress intensity can be explained in different regimes (see, figure 1) as follows
Walker Evans (November 3, 1903 – April 10, 1975) was an American photographer and photojournalist best known for his work for the Resettlement Administration and the Farm Security Administration (FSA) documenting the effects of the Great Depression.
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Supersonic flow encounters a wedge and is uniformly deflected forming an oblique shock. This chart shows the oblique shock angle, β, as a function of the corner angle, θ, for a few constant M 1 lines. The red line separates the strong and weak solutions. The blue line represents the point when the downstream Mach number becomes sonic.
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DAMASCUS/LATAKIA, Syria (Reuters) -Syrian Christians attended regular Sunday services for the first time since the dramatic overthrow of President Bashar al-Assad a week ago, in an early test of ...