Langley Aerothermodynamics Laboratory (LAL)NASA Langley Research Center |
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Test Section and Performance |
Langley Aerothermodynamics Laboratory Characteristics |
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The Langley Aerothermodynamics Laboratory is a collection of four hypersonic wind tunnels utilized for basic fundamental flow physics research, aerodynamic performance measurements, and aeroheating assessment, optimization, and benchmarking of advanced space transportation vehicles. Collectively, they provide a wide range of Mach number, unit Reynolds number, and normal shock density ratio (see table below. The LAL facilities are relatively small and economical to operate, hence ideally suited for fast-paced aerodynamic performance and aeroheating studies aimed at screening, assessing, optimizing, and bench-marking (when combined with computational fluid dynamics) advanced aerospace vehicle concepts and basic fundamental flow physics research. The LAL facilities were designed and constructed in the late 1950's and early 1960's. The LAL has contributed to most major hypersonic vehicle programs including the Apollo, Viking, Space Shuttle Orbiter, National Aero-Space Plane, Pegasus XL, DC-X/Vertical Takeoff and Landing Vehicle, X-33/Advanced Technology Demonstrator, X-34/Small Reusable Booster, X-38/Experimental Crew Return Vehicle, Kistler/Small Payload to Orbit Vehicle, Reusable Launch Vehicle, and X-43/HyperX. The LAL has also been a major contributor to the Columbia Accident Investigation and the Shuttle Return To Flight Program. With the renewed interest in planetary and space exploration, the LAL has also contributed in this arena to the development of the Mars Microprobe, Stardust Sample Return Capsule, Genesis, and Crew Exploration Vehicle. |
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Surface Heating Image of X-34 Acquired with Thermographic Phosphor Technique |
Computational Fluid Dynamic Results of Flowfield Over X-33 Vehicle |
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Data Acquisition and Processing All LAL facilities have compatible, stand-alone data acquisition systems. The heart of the system is a 128 or 256 channel, 16-bit, 50 or 100kHz throughput rate, amplifier per channel, analog-to-digital NEFF System 620/Series 600. PC computers are utilized for acquisition and reduction, and Macintosh computers are available in all control rooms to aid in the post-run plotting and analysis of data. |
Safety and Design Criteria Langley's LHB 1710.15 Wind Tunnel Model System Criteria is the guideline for model design and fabrication. Model installation and any exceptions to this document must have the approval of the LAL Safety Head on a case-by-case basis to assure personnel and tunnel hardware are not exposed to risk. |
Model Supports |
Test Techniques |
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All LAL facilities are equipped with hydraulic model injection/support systems. Angle
of
attack and sideslip ranges are as follows:
Models are typically sting mounted and various dogleg sting holders are available to provide extended angle ranges. Models can also be strut mounted if so desired. Hyper-X Force and Moment Model Installed in the 20-Inch Mach 6 Air Tunnel |
LAL facilities utilize standard water-cooled 6-component strain gage balances and
electronically scanned pressure (ESP) systems. Model surface heat transfer rates are
measured using thin-film resistance gages, infrared imaging systems, thermocouples,
and global two-color thermographic phosphors. The global two-color thermographic phosphor technique is a patented, nonintrusive means for defining a vehicle aeroheating environment quickly and inexpensively. The technique provides qualitative/quantitative heating data over the entire vehicle and is well suited for studying complex boundary layer transition phenomena and extrapolating wind tunnel data to flight conditions. The technique features rapid, inexpensive model fabrication. Standard oil flow techniques are used to observe surface streamline patterns. All facilities except the 31-Inch Mach 10 Air are equipped with a Schlieren system. |
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Test Request Procedures |
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The first step of the test process is to submit a test request form. The form can be filled out electronically or printed for mailing at the NASA Langley aero Compass website. A posttest questionnaire is also available at this site. Our customers are encouraged to provide feedback to the facility for our continuous improvement process. |
Document Version 1.0 |
Trademark Disclaimer: The use of trademarks or names of manufacturers in this report is for accurate reporting and does not constitute an official endorsement, either expressed or implied, of such products or manufacturers by the National Aeronautics and Space Administration. |
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For more information contact: The Aerothermodynamics Facilities Complex Manager -- NASA Langley Research Center -- Hampton, Virginia 23681-2199 phone: 757-864-5229 | fax: 757-864-8670 | e-mail: wte+fm_20inm6@larc.nasa.gov |
NASA Official Responsible For Content: Pete Jacobs |
Page Curator: Lori Rowland |
Date Last Updated: 07/01/08 |