Establishing Relationship between Pressure & Normal Shocks for Convergent-Divergent Nozzle-

Objective of the present study is to analyze experimentally the pressure variation in a varying area circular passage at different supply pressures and compare these with the theoretical solutions. It has been observed that flow of stream of the normal shock is always supersonic while in downstream is always sub-sonic thus shocks slow down the flow rates by sudden increase in pressure ratios. Shock strength is determined uniquely by the mach no. higher the mach no. of upstream of supersonic flow , greater is the shock strength & lower is downstream subsonic mach no. Theoretically minimum pressure is always present at the throat during subsonic condition. But experimentally the position of minimum pressure might be varied because of variation in the stagnation properties of the fluid. This project also includes flow phenomenon over the entire length of nozzle for varying back pressure.