Interaction of Ultra High Mach Number Jets.

Abstract : An experimental and theoretical examination of the shock wave structure and flow variables in the interaction region of two high Mach number air jets was accomplished. A special wind tunnel facility was assembled to include two axisymmetric nozzles with the angle between the nozzle center lines adjustable to 5, 10, 15 deg. The experimental studies were also conducted with various jet Mach numbers, i.e., a Mach 9 primary jet impinged by a Mach 7, 9, 11 jet. A theoretical analysis was also conducted to estimate the angle of impingement and slip stream length, thereby aiding the sizing analysis required for the construction of this special test facility.