Microcomputer based controller for the Langley 0.3-meter Transonic Cryogenic Tunnel

Cover of: Microcomputer based controller for the Langley 0.3-meter Transonic Cryogenic Tunnel |

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

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Subjects:

  • Control systems design,
  • Cryogenic wind tunnels,
  • Feedback control,
  • Microcomputers,
  • Transonic wind tunnels,
  • Wind tunnel tests

Edition Notes

Book details

StatementS. Balakrishna, and W. Allen Kilgore.
SeriesNASA contractor report -- 181808., NASA contractor report -- NASA CR-181808.
ContributionsKilgore, W. Allen., Langley Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15407979M

Download Microcomputer based controller for the Langley 0.3-meter Transonic Cryogenic Tunnel

Flow control of the Langley meter Transonic Cryogenic Tunnel (TCT) is a multivariable nonlinear control problem. Globally stable control laws were generated to hold tunnel conditions in the presence of geometrical disturbances in the test section and precisely control the tunnel states for small and large set point changes.

Get this from a library. Microcomputer based controller for the Langley meter Transonic Cryogenic Tunnel. [S Balakrishna; W Allen Kilgore; Langley Research Center.].

Microcomputer based controller for the Langley meter Transonic Cryogenic Tunnel. By W. Allen Kilgore and S. Balakrishna. Abstract. Flow control of the Langley meter Transonic Cryogenic Tunnel (TCT) is a multivariable nonlinear control problem.

Microcomputer based controller for the Langley 0.3-meter Transonic Cryogenic Tunnel book stable control laws were generated to hold tunnel conditions in the presence of Author: W.

Allen Kilgore and S. Balakrishna. Modeling and control study of the NASA meter transonic cryogenic tunnel for use with sulfur hexafluoride medium - Kindle edition by NASA, National Aeronautics and Space Administration. Download it once and read it on your Kindle device, PC, phones or tablets.

Use features like bookmarks, note taking and highlighting while reading Modeling and control study of the NASA meter transonic Author: National Aeronautics and Space Administration NASA.

The NASA Langley m Transonic Cryogenic Tunnel was modified into operate with any one of the three test gas media viz., air, cryogenic nitrogen gas, or sulfur hexafluoride gas. This document provides the initial test results with respect to the tunnel performance and tunnel control, as a part of the commissioning activities on the microcomputer based by: 2.

Full Description: The Langley Meter Transonic Cryogenic tunnel (m TCT) is used for testing two-dimensional airfoil sections and other models at high. Attention is given to its application to data from the NASA m Transonic Cryogenic Tunnel Adaptive Test Section, for two sizes of a NACA airfoil and to simulated data for an inviscid two.

R. Hall, Onset of condensation effects as detected by total pressure probes in the Langley meter transonic cryogenic tunnel.

NASA Technical Memo (). Kilgore, Special course on advances in cryogenic wind tunnel technology, von Km Institute, Rhode-SaintGene, Belgium. AGARD Report No.

"Application of FLEET Velocimetry in the NASA Langley meter Transonic Cryogenic Tunnel." AIAA31st AIAA Aerodynamic Measurement Technology and Ground Testing Conference, AviationDallas, TX, June Peters, Christopher J., Paul M. Danehy, Brett F. Bathel, Naibo Jiang, Nathan D.

Calvert, and Richard B. Miles. A new fan-driven transonic cryogenic tunnel being built at the NASA Langley Research Center will provide an order of magnitude increase in Reynolds number capability over exisiting U.

transonic tunnels when construction is completed later this year. REFERENCES Goodyer, M. and Kilgore R. Tunnel". NASA Contractor Report ,t Microcomputer Based Controller for the Langley Meter Transonic Cryogenic Tunnel (i_ASl-Clt- 18 18C8) I_IC_CCC E[l_li_ _JSED.

This paper opens with a brief review of cryogenic wind tunnels and their use for high Reynolds number testing. Emphasis is on operational and aerodynamic testing experience in the NASA Langley m Transonic Cryogenic Tunnel (TCT).

Since we built the m TCT init has logged over hours of running at cryogenic temperatures. The NASA Langley m Transonic Cryogenic Tunnel was modified into operate with any one of the three test gas media viz., air, cryogenic nitrogen gas, or sulfur hexafluoride gas.

Balakrishna S () Microcomputer based controller for the Langley meter Transonic Cryogenic Tunnel. National Aeronautics and Space Administration, Langley Research Center. National Technical Information Service, distributor, Hampton, Springfield. The NASA Langley m Transonic Cryogenic Tunnel was modified into operate with any one of the three test gas media viz., air, cryogenic nitrogen gas, or sulfur hexafluoride gas.

This document provides the initial test results with respect to the tunnel performance and tunnel control, as a part of the commissioning activities on the. A Computational Study of Transonic Wall Interference for High Aspect Ratio Wind Tunnel Models at Sideslip Using Wings-Level-Yaw and Pitch-Roll Attitude Techniques William C.

NASA Langley Research Center meter transonic cryogenic wind tunnel T-P/Re-M controller manual. 1 v. (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet Resource: All Authors / Contributors: S Balakrishna; W Allen Kilgore; Langley Research Center.and B.B Gloss, The U.S National Transonic Facility, Special course in cryogenic wind tunnel technology, von Karman Inst, AGARD R ().

Google Scholar 3. Open cavities exposed to transonic flow exhibit large pressure fluctuations which can result in damage to stores or components carried within the cavity.

This study investigates the use of a passive resonant absorber based on Helmholtz resonators to attenuate the unsteady pressure fluctuations that arise in such cavity flows. The NASA Langley m Transonic Cryogenic Tunnel is to be modified to operate with sulfur hexafluoride gas while retaining its present capability to operate with nitrogen.

The modified tunnel will provide high Reynolds number flow on aerodynamic models with two different test : National Aeronautics and Space Administration NASA. The Cryogenic Wind Tunnel Concept for High Reynolds Number Testing; Technical Note NASA-TN-D; NASA: Washington, DC, USA, Kilgore, R.A.

Design Features and Operational Characteristics of the Langley Meter Transonic Cryogenic Tunnel; National Technical Information Service: Alexandria, VA, USA, Britcher, C.

"Instructional course related to calibration of the NASA Transonic Dynamics Tunnel" $8, - Britcher, C. "Development of Low Drag Heat Exchangers for High Altitude Atmospheric Science Aircraft" $25, - Britcher, C. "Large Angle Magnetic Suspension Test Fixture" $, - American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA microcomputer based controller.

The tunnel can provide precise and stable control in temperature to _Langley Meter Transonic Cryogenic Tunnel was established in (reference-I) to prove the concept that cooling the test gas in a closed circuit tunnel. It is a transonic ( cryogenic tunnel with a closed tunnel circuit and has a test section of × m.

To obtain high Reynolds number flow, the flow temperature in the tunnel can be varied in the range K tunnel, and the pressure can be changed in the range kPa. temperature of the air to − °C (− °F), such as the meter (12 in) Transonic Cryogenic Tunnel at NASA Langley Research Center.

However, if a facility However, if a facility Matador Automatic Radar Control (2, words) [view diff] exact match in snippet view article find links to article. Flow Visualization in the Meter Transonic Cryogenic Tunnel • Headline style capitalization is used for proper nouns (see section ).

As a matter of preferred style, the following elements are capitalized in headline style in Langley reports: • Displayed (not run-in) headings • Table titles: Table IV.

Test Results for HP Table IV. As an example, perhaps an aerospace company needs to test a new wing shape. According to the similitude requirements the test must be carried out in a wind tunnel that can drop the temperature of the air to − °C (− °F), such as the meter (12 in) Transonic Cryogenic Tunnel at NASA Langley Research Center.

Tracy and E. Plentovich, “ Characterization of cavity flow fields using pressure data obtained in the Langley meter transonic cryogenic tunnel,” NASA Technical Memorandum No.Google Scholar; M.

Gharib and A. Roshko, “ The effect of flow oscillations on cavity drag,” J. Fluid Mech. (). Results of the AFRSI rewaterproofing systems screening test in the NASA/AMES Research Center (ARC) 2x2-foot transonic wind tunnel (OS) / by: Marroquin, J., et al.

Published: () Theoretical and experimental study of flow-control devices for inlets of indraft wind tunnels by: Ross, James C. Published: (). A simplified fourwall interference assessment procedure for airfoil data obtained in the Langley meter transonic cryogenic tunnel / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch, ), by A.

Murthy and Langley Research Center (page images at HathiTrust). An illustration of an open book. Books. An illustration of two cells of a film strip. Video. An illustration of an audio speaker. Audio. An illustration of a " floppy disk. Full text of "Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle".

Scale models are used in many fields including engineering, architecture, film making, military command, salesmanship and even fun in hobby model building. While each field may use a scale model for a different purpose, all scale models are based on the same principles and must meet the same general requirements to be functional.

Sidewall boundary-layer measurements with upstream suction in the Langley meter Transonic Cryogenic Tunnel / (Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Division, ), by A.

Murthy and Langley. Walter L. Snow, Alpheus W. Burner and William K. Goad, Improvement in the Quality of Flow Visualization in the Langley Meter Transonic Cryogenic Tunnel, NASA TM, Augustpp.

Dal V. Maddalon and William A. Poppen, Jr., Design and Fabrication of Large Suction Panels With Perforated Surfaces for Laminar Flow Control Testing in a.

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