Investigation of Nozzle External Flow.
Final rept. 15 May 74-31 Oct 75,
NEW YORK UNIV WESTBURY AEROSPACE AND ENERGETICS LAB
Pagination or Media Count:
The results of an experimental investigation of the transonic flow over a turbojet boat-tail including the effects of the nozzle exhaust flow are presented. A new type of transonic facility with controllable infection and porosity at the tunnel wall was developed. It was used in the present investigation to simulate accurately both the inviscid and viscous flow fields so as to best represent the complex interaction prevalent at these conditions. The operation and performance of the facility is described here. The AGARD 15 degrees boat-tail nozzle was used in the present study since the flow field over this nacelle has been reported extensively by several investigators. Therefore it established a reference configuration that serves to check proper facility operation and for comparison of the results. The present tests were conducted at a Mach number of approximately .90 in a test section of 23.25 inch 59.0 cm diameter. Detailed measurements of the static pressure distribution on the boat-tail in the facility indicate a significant upstream movement of the separation point and shock with small to moderate changes in the nozzle pressure ratio while increases in the Reynolds number cause a downstream movement of the separation point and of the shock wave.
- Test Facilities, Equipment and Methods
- Fluid Mechanics
- Jet and Gas Turbine Engines