Accession Number:

ADA056945

Title:

Design and Test of an Annular Sting Support Concept for Aftbody Nozzle Wind Tunnel Testing.

Descriptive Note:

Final rept. 1 Jan 76-1 Sep 77,

Corporate Author:

AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

• Bowers,Douglas L.

Report Date:

1978-04-01

Pagination or Media Count:

72.0

Abstract:

The annular sting support concept for aftbody nozzle testing supports the model through the exhaust nozzles, provides high pressure air to simulate the exhaust plume to enter the model, and provides a path for instrumentation lines to be routed out of the model. The support concept, experimental model, and supporting analytical studies are described. Experimental data for the aftbody nozzle contours are compared for a free jet test and the annular sting support test. Also the results of an analytical prediction of the nozzle boattail pressure distribution and wind tunnel wall effects are described. Test results and experimental data comparisons indicate that the annular sting support concept offers an alternate testing technique for aftbody nozzles. Author

Descriptors:

• *STING MOUNTS
• *AFTERBODIES
• *TURBOJET EXHAUST NOZZLES
• SIMULATION
• TURBOFAN ENGINES
• MATHEMATICAL PREDICTION
• WIND TUNNEL TESTS
• EXHAUST PLUMES
• NOZZLE GAS FLOW
• WIND TUNNEL MODELS
• TRANSONIC FLOW
• TURBOJET ENGINES
• BOATTAIL AFTERBODIES

Subject Categories:

• Test Facilities, Equipment and Methods
• Fluid Mechanics
• Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE