Last edited by Mesar
Wednesday, August 5, 2020 | History

3 edition of Semi-span model testing in the National Transonic Facility found in the catalog.

Semi-span model testing in the National Transonic Facility

Semi-span model testing in the National Transonic Facility

annual status report, August 1995, cooperative agreement no. NCC1, 169

  • 364 Want to read
  • 8 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Computational fluid dynamics.,
  • Computational grids.,
  • Navier-Stokes equation.,
  • Semispan models.,
  • Wind tunnel models.,
  • Wind tunnel tests.

  • Edition Notes

    Statementprincipal investigator: Ndaona Chokani.
    SeriesNASA contractor report -- NASA CR-199272.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17684791M

    Engineers at NASA’s Langley Research Center in Hampton, Va., recently installed this percent scale model based on a possible future aircraft design by the Boeing Company in its Transonic Dynamics Tunnel. The foot model is “semi-span,” meaning it looks like a plane cut in half. Transonic Dynamics Tunnel engineers at Langley installed a foot semispan Boeing model to assess the aeroelastic qualities of an unusual trussbraced wing configuration. Aeroelasticity is .

    AIAA Excel/VBA for Numerical Methods Education, Calculations and Applications in Energy Engineering Considerations for Aerodynamic Testing of Scaled Runback Ice Accretions (AIAA ) Whalen, E. A AIAA A Transonic Axial Compressor Facility for Fundamental Research and Flow Control Development. National Emergency Library. Top American Libraries Canadian Libraries Universal Library Community Texts Project Gutenberg Biodiversity Heritage Library Children's Library. Open Library. Featured movies All video latest This Just In Prelinger Archives Democracy Now! Occupy Wall Street TV NSA Clip Library.

    Full text of "Results of tests using a scale model (OTS) of the Space Shuttle integrated vehicle in the AEDC 16 foot transonic propulsion wind tunnel (IAA), volume 1" . Figure show sa model with a batten reinforced (BR) wing ready for testing in the wind tunnel. The models were equipped with controls and operational servo actuators for tests.


Share this book
You might also like
Old School

Old School

Certification/enforcement analysis

Certification/enforcement analysis

Iqbal and Modern Era

Iqbal and Modern Era

A general survey of new villages

A general survey of new villages

Reshaping the Inner You

Reshaping the Inner You

University traditions

University traditions

History of Marshall Field & Co., 1852-1906.

History of Marshall Field & Co., 1852-1906.

On literature and art

On literature and art

Volunteerism in state government

Volunteerism in state government

Open water lifesaving awards & lifesaving awards

Open water lifesaving awards & lifesaving awards

Advanced sales management handbook and cases

Advanced sales management handbook and cases

Social conflict and political unrest in Bengal

Social conflict and political unrest in Bengal

Power and international order

Power and international order

Concise physics for ancillary degree students.

Concise physics for ancillary degree students.

Semi-span model testing in the National Transonic Facility Download PDF EPUB FB2

Get this from a library. Semi-span model testing in the National Transonic Facility: annual status report, Octobercooperative agreement no.

NCC1, [Ndaona Chokani; United States. National Aeronautics and Space Administration.]. Get this from a library. Semi-span model testing in the National Transonic Facility: annual status report, Augustcooperative agreement no. NCC1, [Ndaona Chokani; United States.

National Aeronautics and Space Administration.]. Advancement of Semispan Testing at the National Transonic Facility Article in Journal of Aircraft 39(2) March with 12 Reads How we measure 'reads'.

Enhancements to the FAST-MAC Circulation Control Model and Recent High-Reynolds Number Testing in the National Transonic Facility. by Flow Scheme Used in the NTF Semi-Span FAST-MAC Model. by Gregory S. Jones | Jan 1, Paperback More Buying Choices $ (1 used offer) FastMac ACE U-Socket Decorator Duplex Dual Outlet Dual USB.

A second wind tunnel test of the FAST-MAC circulation control semi-span model was recently completed in the National Transonic Facility at the NASA Langley Research Cen-ter.

The model allowed independent control of four circulation control plenums producing a high momentum jet from a blowing slot near the wing trailing edge that was directed. NASA's National Transonic Facility can test at much higher Reynolds numbers than the new European Transonic Wind Tunnel (ETW).

However, the National Transonic Facility is primarily a research facility, and it has very low productivity. Washington, DC: The National Academies Press. doi: / 20 million at Mach (full span model) 35 million at Mach (semi-span model) million at Mach 1 (full span model) Mach Number.

The U.S. National Transonic Facility has a Reynolds number capability of million, but its productivity is an order of.

Testing at the National Transonic Facility NASA’s National Transonic Facility (NTF) wind tunnel is a unique research tool that operates over a large range of temperatures, as low as o F using cryogenics (liquid nitrogen), and up to F using warm American Institute of Aeronautics and Astronautics 3File Size: KB.

In support of this need, multiple investigations have been conducted in the National Transonic Facility (NTF) at the NASA Langley Research Center to develop a semi. Full text of "Design study of test models of maneuvering aircraft configurations for the National Transonic Facility (NTF)" See other formats.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA   American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Full text of "NASA Technical Reports Server (NTRS) Transonic Symposium: Theory, Application, and Experiment, volume 1, part 2" See other formats.

configuration was also confirmed at the NASA NTF (National Transonic Facility) at high Mach number and high Reynolds number testing as well (Fig. CS). Ultimately, shock wave strength was reduced and drag diver-gent Mach number was increased for the optimum OTWEM configura-tion while maintaining laminar flow under most flight conditions.

The. The National Transonic Facility (NTF) is a closed loop cryogenic pressure tunnel capable of Mach numbers from tostagnation pressures from 1 to atm, and a maximum unit Reynolds number of ×10 6 ft −1 (×10 6 ft −1) at a Mach number of It has a square m ( ft) test section with a length of m (25 ft).Cited by: NASAtmpdf - Raymond E.

Mineck and Odis C. Pendergraft, Jr., Test-to-Test Repeatability of Results From a Subsonic Wing-Body Configuration in the National Transonic Facility, NASA/TM, March(1MB). Init became the Thomas Jefferson National Accelerator Facility, better known as Jefferson Lab.

The images above show the space radiation lab in. Raymond E. Mineck and Odis C. Pendergraft, Jr., Test-to-Test Repeatability of Results From a Subsonic Wing-Body Configuration in the National Transonic Facility, NASA/TM, March(1MB) - Pages: National Aeronautics and Space Administration Office of Communications History Program Office Washington, DC ii Library of Congress Cataloging-in-Publication Data (Revised for vol.

8) NASA historical data book. (NASA SP- ) Vol. 1 is a republication of NASA historical data book, –/ Jane Van Nimmen and Leonard C.

Bruno. Read NASA's Contributions to Aeronautics, Volume 1, by National Aeronautics & Space Administration. in HTML for FREE. Also available in PDF, ePub.

Raymond E. Mineck, Lewis R. Owens, Jr., Richard A. Wahls and Judith A. Hannon, Computer Model To Simulate Testing at the National Transonic Facility, NASA TM, Augustpp. H. M. Ross, S. P. Fears and T.

M. Moul, Low-Speed Wind-Tunnel Investigation of the Stability and Control Characteristics of a Series of Flying Wings With Sweep. These systems should include provisions for combining these data into the regular stream of test data provided by a given facility.

Model Attitude and Position Monitoring - Measurements of wind tunnel model attitude and position (e.g., roll, pitch, yaw angles and spatial coordinates X, Y, Z relative to a defined origin and coordinate system.In his book, Fluid Dynamics of Drag, Hoerner presents a series of wing tip shapes which had been previously tested in Germany and documented in the USA by Hoerner, Fig.

tests were carried out in a low speed wind tunnel on model-scale wings of relatively low aspect ratio fitted with different tip by: