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The Design of a High-Q, MACH-5 Nozzle for the Langley 8-Foot HTTA new nozzle has ben designed for the NASA Langley Research Center 8-Foot High Temperature Tunnel. The new nozzle was designed with a Mach-5 exit flow at a Mach-5 flight-enthalpy test condition and has a smaller throat area than the existing Mach-5 nozzle which significantly increases the range of dynamic pressures that can be achieved in the facility. The nozzle was designed using the NASA Langley IMOCND computer program which solves the potential equation using the classical method of characteristics. Several axisymmetric nozzle contours were generated and evaluated using viscous computational fluid dynamics. A number of items were considered in the evaluation, including flow uniformity, thermal and structural design, manufacturing schedule and cost. Once the final contour was selected, studies were done to determine the effects of manufacturing irregularities (steps and cavities at joints). These studies were done to develop manufacturing specifications and assembly tolerances.
Document ID
20060022183
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Gaffey, Richard L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Stewart, Brian K. (NASA Langley Research Center Hampton, VA, United States)
Harvin, Stephen F. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 23, 2013
Publication Date
January 1, 2006
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
AIAA Paper 2006-2954
Meeting Information
Meeting: 25th AIAA Aerodynamic Measurement Technology and Ground Testing Conference
Location: San Francisco, CA
Country: United States
Start Date: June 5, 2006
End Date: June 8, 2006
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 489-02-07-07
Distribution Limits
Public
Copyright
Public Use Permitted.

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