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1’ x 1’ Supersonic Wind Tunnel

The 1- by 1-foot Supersonic Wind Tunnel (SWT) specializes in conducting fundamental research in supersonic and hypersonic fluid mechanics, supersonic-vehicle-focused research and detailed benchmark quality experiments for Computational Fluid Dynamics (CFD) code validation.

Facility Overview

The 1′ x 1′ Supersonic Wind Tunnel (1×1), located in the Engine Research Building (ERB), is one of the most active test facilities at the NASA Glenn Research Center. Used to conduct fundamental research in supersonic and hypersonic fluid mechanics, it is also used for supersonic-vehicle-focused research and detailed benchmark quality experiments for CFD code validation.

The tunnel can provide continuous operation at 10 discrete airspeeds between Mach 1.3 and 6.0 by using an appropriate fixed-area contoured nozzle block upstream of the test section.

A number of specialized support systems are available to meet the research customer’s needs such as auxiliary bleed, model hydraulics, and probe actuation systems. Model buildup and machine shop equipment also are available to accommodate model changes. The 1×1 SWT uses several different types of experimental research tools that are invaluable to fundamental studies.

Flow can be visualized with the use of schlieren, a sheet-laser system, or blue Zyglo and black lights. Qualitative flow-field measurements can be made with a two-component laser Doppler velocimeter (LDV) and trace gas systems.

The equipment in the 1×1 SWT is complemented by a staff experienced in supersonic test hardware and experimentation. Two-shift staffing and operation provide high productivity, flexibility, and quick model installation and configuration changes. With its capabilities, expert staff, and efficiency, the 1×1 SWT offers the supersonic research community an excellent low-cost tool for fundamental small-scale research.

Quick Facts

The SWT is used to conduct fundamental research in supersonic and hypersonic fluid mechanics. It is also used for supersonic-vehicle-focused research and detailed benchmark quality experiments for CFD code validation.

Name	1′ x 1′ Supersonic Wind Tunnel (1×1)
Mach Number	1.3 – 6.0 (10 discrete airspeeds)
Test Section	1-ft high by 1-ft wide by 8-ft long

• The 1×1 is a valuable tool to conduct fundamental research in supersonic and hypersonic fluid mechanics.
• Specializes in conducting fundamental research in supersonic-vehicle-focused research.
• Offers the supersonic research community an excellent low-cost testing tool for small-scale research.
• A number of specialized support systems, including auxiliary bleed, model hydraulics, and probe actuation systems, are available.

Capabilities

The 1’x1′ Supersonic Wind Tunnel provides customers with a facility capable of conducting fundamental research in supersonic and hypersonic fluid mechanics.

Characteristics and Performance

• Mach Number Range: 1.3 to 6.0 (discrete number)
• Reynolds Number: 0.4 – 16.5 x 106/ft
• Total Temperature: 520 – 1100°R
• Dynamic Pressure: 80 to 1750 lbf/ft2
• Maximum Pressure: 165 psia

Flow Visualization

• Schlieren
• Sheet-laser system
• Blue Zyglo
• Black light

Support Systems

• Model hydraulics
• Auxiliary bleed
• Probe actuation systems

Model Data and Control System Capabilities

• Pressure Systems
  ESP is an off the shelf electronically scanned pressure system. The system consists of numerous 32 port, rack mounted modules from +/-2.5 PSID to +500 PSID, located outside the test chamber. Each module has a check pressure to assure the module is performing correctly and can be calibrated in place using up to 5 highly accurate calibration pressures to maintain the overall system accuracy of +/-0.05% of range. This calibration is performed every 2 hours. For the 1×1, the following ranges are typically provided:
  • 224 ports +/- 5 PSID 5 PSIA Ref
  • 256 ports +/- 15 PSID Barometric Ref
  • 64 +/- 30 PSID Barometric Ref
  • 96 +/- 100 PSID Barometric Ref
  • 32 +/250 PSID Barometric Ref
• Data System – Escort
  • Escort, the steady state data acquisition system, uses a DEC Alpha microprocessor to provide:
    • An X window based system
    • Real time on-line acquisition of analog signals
    • Conversion of raw 10Hz filtered digitized Neff data to engineering units
    • Computed performance calculations, which can be displayed in a variety of tabular and graphical formats.
    • Limit checking on all selected changes
    • 1 second update rate
  • Escort can stand alone to meet all secure test requirements or it can be connected to a central processing cluster, which facilitates software application development, downloading of software, uploading and storage of facility tables, post processing of data and transmitting of data to a data collector for archival storage. For the 1×1, Escort provides the following:
    • Accuracy for the Neff 400 is +/- 0.05% of range
    • 240 channels of which 220 are available for the test article
    • 48 temperatures from type E
• Dynamic Data System
  The transient data system provides multi-channel high speed digitized acquisition of rapidly changing cyclic on non-periodic impulse type events. The system consists of:
• A near real type display capability
• Off loading the data by FTPing, in near real time, to either our computer or yours for post processing
• 48 16 Bit A/D per channel
• Throughput of 9.6 million samples per second

Contact

1×1 Supersonic Wind Tunnel
Facility Manager: Gwynn Severt
216-433-8310
Gwynn.A.Severt@nasa.gov

Testing Division
21000 Brookpark Rd., MS 6-8
Cleveland, Ohio 44135
216-433-8301
William.P.Camperchioli@nasa.gov

If you are unsure about whom to contact about a specific facility question, please call our main number at 216-433-4000.

Using Our Facilities

NASA’s Glenn Research Center provides ground test facilities to industry, government, and academia. If you are considering testing in one of our facilities or would like further information about a specific facility or capability, please let us know.

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