By Tatiana V. Bazhenova
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Extra info for Shock Waves in Real Gases: Course Held at the Department of Hydro-and Gas-Dynamics, July 1970
Sonic. Let us find the boundary of the effect of signals which disturb the region behind the reflected wave. l 0 and find the point of intersection of the reflected wave with a circle of radius a2 • We determine the difference X. A - X. 2 • It may be assumed that the break on the reflected wave which is due to the need for joining the processes of reflection and flow past the vertex of the wedge will take place in point R which defines the region of influence of angular signals in the gas flow behind the reflected wave.
The vertex angles of the wedge were 10, 24, 28, 32 and 36°. 68 · A0 4 dynes/cm2.. The angles between all the waves comprising the Mach configuration were measured on the photographs and their variation in time was checked. The shock wave velocity was measured from the photographs and at the same time by means of piezoelectric pickups placed along the tube. 58 5. Mach reflection The photographs taken in ~olshow clearly that the reflected wave has a break. , a second triple point is formed. The reflected wave is situated below the path of motion of the triple point.
Angles w 2 and w ~ = qo - ( X + li0) for u 0 were obtained experimentally. In argon (Fig. 2,a) the experimentally obtained values of W2 are in agreement wi th curve 3, since no physical or chemical transformations take place in argon under the condi tions und er study. In air in the range of incident-wave velocities of 900-1200 rn/sec the points lie on curve 3. In the velocity range of 1800-2500 rn/sec the relaxation time for exciting molecular vibra tions in time for 0~ 02. and H2 and the dissocia tion is shorter than the time during which the gas is in the heated state, while the dissociation relaxation time for H2 is much greater.
Shock Waves in Real Gases: Course Held at the Department of Hydro-and Gas-Dynamics, July 1970 by Tatiana V. Bazhenova