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Monday, May 11, 2020 | History

3 edition of The NASA Langley 8-foot transonic pressure tunnel calibration found in the catalog.

The NASA Langley 8-foot transonic pressure tunnel calibration

The NASA Langley 8-foot transonic pressure tunnel calibration

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Published by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va .
Written in English

    Subjects:
  • Flow characteristics.,
  • Slotted wind tunnels.,
  • Transonic wind tunnels.,
  • Wind tunnel calibration.

  • Edition Notes

    Other titlesNASA Langley eight-foot transonic pressure tunnel calibration.
    StatementCuyler W. Brooks, Charles D. Harris, and Patricia G. Reagon.
    SeriesNASA technical paper -- 3437.
    ContributionsHarris, Charles D., 1952-, Reagon, Patricia G., Langley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15404518M

    Documents and information from the NASA Network Resource and Training Site. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA

    NASA Langley Research Center. Visitors toured a high-speed wind tunnel, the 8-Foot High Temperature Tunnel and a low-speed tunnel, the byFoot Subsonic Tunnel. They also toured the world’s largest pressurized cryogenic wind tunnel, the National Transonic Facility (NTF). There was, however, a paper by Kilgore et al of NASA Langley (paper 1 of) which not only set out the results of tests in the NASA 1/3 m pilot transonic cryogenic tunnel but also gave details of the planned National Transonic Facility (NTF) to be built at the Langley Research Center, Cited by:

    The Blake W. Corson Jr., Papers are comprised of professional and personal files, correspondence, and published materials from (bulk, ), primarily relating to his career as an engineer at . Unique Testing Capabilities of the NASA Langley Transonic Dynamics Tunnel, an Exercise in Aeroelastic Scaling. Thomas G. Ivanco; Background Pressure Profiles for Sonic Boom Vehicle Testing in the NASA Glenn 8-foot by 6-foot Supersonic Wind Tunnel.


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The NASA Langley 8-foot transonic pressure tunnel calibration Download PDF EPUB FB2

NASA Technical Paper The NASA Langley 8-Foot Transonic Pressure Tunnel Calibration Cuyler W. Brooks, Jr., Charles D. Harris, and Patricia G. Reagon Langley Research Center • Hampton, Virginia National Aeronautics and Space Administration Langley Research Center • Hampton, Virginia August   The NASA Langley 8-Foot Transonic Pressure Tunnel Calibration.

Cuyler W. Brooks, Jr., Charles D. Harris, and Patricia G. Reagon. NASA Technical Paper Aerodynamic Surface Design Methodology. Richard L. Campbell. Applications of a Transonic Wing Design Method. Leigh A. Smith and Richard L. : Langley Research Center.

Get this from a library. The NASA Langley 8-foot transonic pressure tunnel calibration. [Cuyler W Brooks; Charles D Harris; Patricia G Reagon; Langley Research Center.].

Section of "Wind Tunnels of NASA" site describing "The First Big High-Speed Tunnel (8-Foot High Speed Tunnel) Major Contributions to Aviation Achieved in the Langley 8-Foot High-Speed Tunnel and the 8-Foot Transonic Pressure Tunnel.

Pete Jacobs. National Register Nomination. Procedures to Repair 8' HSTCenter: Langley Research Center. The Langley Research Center (LaRC or NASA Langley) located in Hampton, Virginia, United States, is the oldest of NASA's field centers. It directly borders Langley Air Force Base and the Back River on the Chesapeake has focused primarily on aeronautical research, but has also tested space hardware at the facility, such as the Apollo Lunar arters: Hampton, Virginia, United States.

DESCRIPTION AND CALIBRATION OF THE LANGLEY 6- BY INCH TRANSONIC TUNNEL Charles L. Ladson Langley Research Center SUMMARY The Langley 6- by inch transonic tunnel is a two-dimensional facility with slotted top and bottom walls, which. Credit: NASA/Sean Smith.

Click on the image for a larger view There's more sadness to come. Next fiscal year, the Foot Transonic tunnel is going to join the 7-by in the archives. So are two 8-Foot tunnels. The year after that, the byFoot Full-Scale tunnel on Langley's East Side is scheduled to go.

The National Transonic Facility (NTF) at Langley is a high pressure, cryogenic, closed-circuit wind tunnel with a Mach number range from to and a Reynolds number range of 4 x 10 6 to x 10 6 per foot.

The test section has 12 slots and 14 reentry flaps in the ceiling and floor. This paper concerns one of the NASA in-house activities, the Langley Laminar Flow Control (LFC) Project, which was carried out in the Langley 8-foot Transonic Pressure Tunnel (8-ft TPT).

The idea for such an undertaking came from Dr. Werner Pfenninger in and stemmed, primarily, from a desire to know more about the compatability of a high Cited by: 3. 8-Foot Transonic Pressure Tunnel (TPT): Sample of Schlieren results Left - Mach # = Right - Mach # = The photograph shows the Energy Efficient Transport (EET) Model in the NASA-Langley Research Center 8-Foot Transonic Pressure Tunnel.

The model has been tested. A NASA Langley technical paper identifies the ultimate source of the slotted-wall solution that NACA Langley devised for the transonic tunnel problem in the late s: "The first 30 years of wind tunnel wall-interference research yielded an important fact for modern wind tunnels; that is, theoretically and experimentally, solid-wall.

Several large components of the full scale tunnel and smaller historic artifacts from the full scale and the 8-foot transonic pressure tunnel were salvaged for display at NASA Langley and other. In the past, only a relatively small number of investigations were conducted using hot-wire anemometry in transonic and subsonic slip flows.

This was due to the complexity of the applicable equations. Now it appears that the developments in electronics and computational methods have made it practical to reconsider this by: The Eight-Foot High Speed Tunnel is a single-return atmospheric pressure tunnel with an 8-foot diameter closed-throat test section.

The tunnel became operational in and at that time had a maximum speed of Mach driven by an 8,horsepower electric motor/fan. Pressure Calibration and Testingwould channel the air around a test subject and allow the gathering of valuable transonic research data. Langley’s 8-Foot and Foot High Speed Tunnels.

Guide to NACA Historical Sources at Langley [] Since this book is amply footnoted by chapter, and since so little is generally known about the recently constituted archives that provided most of my source material, I have chosen to provide readers with the following general-purpose guide to the major sources for research into NACA history at NASA Langley Research Center instead of with the.

NASA Langley research center's high temperature wind tunnel is used to test hypersonic aircraft as well as reentry systems and thermal protection systems. It is capable of sustaining speeds of.

NASA Langley Research Center Tours. Two tours of the NASA Langley Research Center will offered during TFAWS Each tour will visit three sites, possibly including the National Transonic Facility, Inch Mach 10 Air Tunnel, Impact Dynamics Research Facility and the 8-Foot High Temperature Tunnel (tour stops are subject to change and will depend on the size of the tour group).

A brief description of these disturbance control features is given for the low turbulence pressure tunnel, the 4 x 7 meter tunnel, and the 8 foot transonic pressure tunnel. The 8-Foot Transonic Pressure Tunnel was completed in the East Area in and became known as “Whitcomb’s Tunnel” after famed Langley aerodynamicist Richard "Dick" Whitcomb.A 1/2-scale model of a portion of the NASA Langley 8-foot transonic pressure tunnel was used to conduct some turbulence reduction research.

The experimental results are correlated with various. The last major wind tunnel accident at NASA Langley occurred inwhen a chunk of metal broke from a piece of machinery and destroyed fan blades in the Foot Transonic Tunnel.