Flow Characteristics of Straight and Slanted Entry Nozzle Run by a Supersonic Stream

An experimental study was conducted on 15° slanted entry nozzle to compare with same geometry straight entry Convergent-Divergent (CD) nozzle. The nozzle with design Mach number of 2.94 placed in a Mach 1.8 flow reveals that the nozzle can choke and deliver supersonic flow at its exit. In this paper the wall static pressure distribution along the length of the straight and slanted entry nozzle and its comparison with isentropic flow is discussed. The tests were conducted at different Nozzle Pressure Ratios (NPR) of the driving nozzle ranging from 3 to 7. The variation of inlet and exit Mach numbers for both straight and slanted entry nozzles run by a supersonic stream is also discussed. The separation location obtained by present experiment and from other empirical relations is compared.