Last edited by Goltigar
Sunday, July 26, 2020 | History

6 edition of Wind Tunnel and Propulsion Test Facilities found in the catalog.

Wind Tunnel and Propulsion Test Facilities

Supporting Analyses to an Assessment of NASA"s Capabilities to Serve National Needs

by Philip S. Anton

  • 399 Want to read
  • 19 Currently reading

Published by RAND Corporation .
Written in English

    Subjects:
  • Technology,
  • United States,
  • Research,
  • General,
  • Technology & Industrial Arts,
  • Testing,
  • Science/Mathematics,
  • Aeronautics & Astronautics,
  • Non-Classifiable,
  • Airplanes,
  • Wind tunnels,
  • Industrial Technology,
  • Aeronautics,
  • National Aeronautics and Space

  • The Physical Object
    FormatPaperback
    Number of Pages138
    ID Numbers
    Open LibraryOL8188424M
    ISBN 100833036424
    ISBN 109780833036421

    NASA Langley Research Center, 8-Foot Transonic Pressure Tunnel, Thornell Avenue, Hampton, Hampton, VA Photo(s): 12 | Data Page(s): 17 | Photo Caption Page(s): 2 Contributor: Newbill, Michael - Anderson, Richard K, Jr - Laird, Matthew R - Mattson, Axel T - Cunningham, Chris - Dutton, David H - National Advisory Committee for Aeronautics - Draley, Eugene C - Wright, Ray H - Flechner, Stuart. Advanced Hypersonic Test Facilities. Frank K. Lu Aerodynamic and Propulsion Test Unit. Planned Mid and FarTerm Incremental APTU Test enthalpy flight conditions flowfield ground test guideway heat flux heat transfer helium high-enthalpy high-pressure hypersonic test Hypersonic Wind Tunnel hypervelocity HYPULSE increase initial.

    Closed circuit wind tunnel (WT1) Dimensions (height x width x length): x x m Max. flow velocity: 70 m/s. This Eiffel open-loop wind tunnel has a contraction ratio and is driven by a hp centrifugal fan, enabling velocities up to mph in the modular 3-foot by 3-foot test section. Propeller dynamometer, gas turbine engine and piston engine test stands specially designed for this facilty allow for a variety of test arrangements, including.

    Calspan’s Transonic Wind Tunnel is a continuous flow, variable density, closed-circuit wind tunnel testing facility with an 8 x 8 foot [ x meter] test section. Test conditions are achieved through independent control of Mach number and one other pressure-dependent variable for constant Reynolds number, static pressure, dynamic. home reference library technical articles manufacturing and process equipment chapter the nasa langley research center 8-ft high temperature tunnel Advanced Hypersonic Test Facilities This book presents a number of new, innovative approaches to satisfy the enthalpy requirements for air-breathing hypersonic vehicles and planetary entry problems.


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Wind Tunnel and Propulsion Test Facilities by Philip S. Anton Download PDF EPUB FB2

: Wind Tunnel and Propulsion Test Facilities: Supporting Analyses to an Assessment of NASA's Capabilities to Serve National Needs (): Anton, Philip S.: BooksCited by: 7. Wind Tunnel and Propulsion Test Facilities and millions of other books are available for Amazon Kindle.

Learn more. Wind Tunnel and Propulsion Test Facilities: An Assessment of NASA's Capabilities to Serve National Needs 0th Edition Cited by: 6. The wind tunnel test facility has been designated a landmark by the American Society of Mechanical Engineers because of its engineering significance.

Propulsion Wind Tunnel 16T 16T is a Wind Tunnel and Propulsion Test Facilities book wind tunnel that can be configured for Mach numbers from to It is primarily used to test aerodynamics, propulsion integration, and weapons Branch: US Air Force.

Wind Tunnel and Propulsion Test Facilities An Assessment of NASA’s Capabilities to Serve National Needs by Philip S. Anton, Eugene C. Gritton, Richard Mesic, Paul S. Steinberg, Dana J. Johnson, Michael Block, Michael Scott Brown, Jeffrey A.

Drezner, James Dryden, Thomas Hamilton, Thor Hogan, Deborah Peetz, Raj Raman, Joe Strong Cited by: 6. Given their ubiquitous nature and utility, a wind-tunnel design project is a fairly common yet complex exercise.

We therefore review in this article the fundamentals of low-speed wind-tunnel design. The Other Format of the Wind Tunnel and Propulsion Test Facilities: Supporting Analyses to an Assessment of NASA's Capabilities to Serve National Needs by Get FREE SHIPPING on Orders of $35+ Customer information on COVID B&N Pages: Table of Contents for Wind tunnel and propulsion test facilities: supporting analyses to an assessment of NASA's capabilities to serve national needs / Philip S.

Anton. Low-speed, atmospheric, non-return, induction-type facility. Typical models include engine inlets, exhaust nozzles, small engines or powered vehicles, aerodynamic half or full models, as well as thrust reversers. #N#Cal Poly's Low- Speed Wind Tunnel. #N#L 14 ft x W 4 ft x H 3 ft (L m x W m x H m).

Get this from a library. Wind tunnel and propulsion test facilities: supporting analyses to an assessment of NASA's capabilities to serve national needs.

[Philip S Antón; United States. National Aeronautics and Space Administration.; Rand Corporation.; United States. Department of Defense. Office of the Secretary of Defense.;] -- The National Aeronautics and Space Administration's (NASA's.

The 9-foot by 9-foot Propulsion Wind Tunnel is a non-return, induction-type facility that is set up primarily for inlet and aerodynamic testing, but it is easily adapted to other uses. It has extensive photographic and video equipment for monitoring and recording model configuration, flow.

This technical report supports a companion monograph (Wind Tunnel and Propulsion Test Facilities: An Assessment of NASA's Capabilities to Serve National Needs, MGNASA/OSD), providing more detailed data, observations, and conclusions about the future of.

10×10 Abe Silverstein Supersonic Wind Tunnel. The by Foot Abe Silverstein Supersonic Wind Tunnel (10×10) is the largest and fastest wind tunnel facility at NASA’s Glenn Research Center and is specifically designed to test supersonic propulsion components from inlets and nozzles to full-scale jet and rocket engines.

Get this from a library. Wind tunnel and propulsion test facilities: an assessment of NASA's capabilities to serve national needs. [Philip S Antón;] -- The National Aeronautics and Space Administration's (NASA's) wind tunnel and propulsion test facilities continue to be important to U.S.

competitiveness across the military, commercial, and space. Wind Tunnel and Propulsion Test Facilities: MGOSD/NASA by Philip S. Anton,available at Book Depository with free delivery worldwide.5/5(1).

In most past programs, wind tunnel test results have often been lost or inadequately documented for future use. The authors feel that the extensive Space Shuttle wind tunnel test program should be considered as a national resource.

It is with that thought in mind that the entire Space Shuttle wind tunnel test data base has been archived in both. This research brief describes work done by the RAND National Defense Research Institute documented in Wind Tunnel and Propulsion Test Facilities: An Assessment of NASA’s Capabilities to Serve National Needs, by Philip S.

Antón et al., MGNASA/OSD,pp., ISBN:(Full Document), and in Wind Tunnel and Propulsion Test. An Internet Book on Fluid Dynamics Wind Tunnels If the prototype Mach number, M, is lower than aboutthen subsonic wind tunnel testing may be appropriate and the primary focus should be the Reynolds number scaling.

If the intention is to employ a small scale model of the device or to test the device or model at non-prototypical wind speeds File Size: KB. The National Aeronautics and Space Administration's (NASA's) major wind tunnel (WT), propulsion test (PT), and simulation facilities exist to serve NASA's and the nation's aeronautics needs.

Together with the K-Site facility, these facilities compose the Cryogenic Test Complex. + View site: Hypersonic Tunnel Facility (HTF) A unique wind tunnel designed to test air-breathing propulsion systems at speeds exceeding 5 times the speed of sound.

+ View site. In a wind tunnel, the axial centerline of the test section defines the direction of the oncoming wind-the aerodynamic equivalent of the flight path. The ease of measuring aerodynamic forces relative to the tunnel axis on a model held stationary in the airstream opened a new era in.

An experimental scale model of the B plane is prepared for wind tunnel tests in the plant of North American Aviation, Inc., Inglewood, Calif. This plant produced the B bomber. California Inglewood United States, What is the National Wind Tunnel Facility? The National Wind Tunnel Facility (NWTF) (EPSRC grant EP/L/1) is an initiative in which 23 tunnels distributed across 12 UK universities (host institutions) are made open access (for up to 25% of time) to external users, both university and industry based.

The scheme which is aimed at keeping the UK at the forefront of aerodynamic and fluid.SSTI TEST FACILITIES CAPABILITY HANDBOOK STENNIS SPACE CENTER and MARSHALL SPACE FLIGHT CENTER Rocket Propulsion Test Program Office Building File Size: 3MB.