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3 edition of Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle found in the catalog.

Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle

Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle

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Published by MCAT Institute, National Aeronautics and Space Administration, National Technical Information Service, distributor in San Jose, CA, [Washington, DC, Springfield, Va.? .
Written in English

    Subjects:
  • Supersonic wind tunnels.

  • Edition Notes

    StatementStephen W.D. Wolf.
    Series[NASA contractor report] -- NASA CR-194548., NASA contractor report -- NASA CR-194548.
    ContributionsUnited States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14700996M

    However, in order for relaminarization to be a viable technique for a quiet tunnel, the residual turbulence in the relaminarized boundary layer must be very small since the sources of the free-stream sound disturbances are clearly the convected turbu- lent eddies in the supersonic boundary-layer flow. Boundary Layer in the Nozzle of an Intermittent Axisymmetric Hypersonic Wind Tunnel BY N Wood A characteristic of hypersonic urn&tunnel nozzles is the development of a thick boundary layer along the walls, thus severely restricting the core In an intermittent wind tunnel with a very short running tzme (e.g., the File Size: KB.

    wind tunnel data. The wind tunnel geometry and tunnel constraints were employed in accordance with the method of characteristics technique to design the supersonic nozzle profiles. The Sivells’ nozzle design method was deemed the most feasible which calculates the . supersonic wind tunnel (continuous) A suction-type continuous-operation supersonic wind tunnel for investigations into subsonic and supersonic air flow. It also allows students to study air flow in two dimensions around aerodynamic models.

    An extensive scheme for the design, fabrication, and realization of an intermittent blow-down supersonic wind tunnel for laboratory experiments is proposed in this paper. Special attention was given to startup and the transient performance of the tunnel. Pope and Goin [3] provide an extensive reference for the testing of high-speed wind tunnels. Flow quality studies of the NASA Lewis Research Center 8- by 6-foot supersonic/9- by foot low speed w User manual for NASA Lewis by Foot Supersonic Wind Tunnel [microform] / Ronald H. Soeder; Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle [microform] / Stephen W.D.


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Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle Download PDF EPUB FB2

Of a cryogenic adaptive nozzle to generate Quiet (low disturbance) supersonic flow. The work under this contract can be summarized as follows: 1) Research to find a unique drive system for the Fluid Mechanics Laboratory (FML) Laminar Flow Supersonic Wind Tunnel (LFSWT) using a pilot tunnel.

2) Supportive effort for ongoing Proof of Concept (PoC) research. (low-disturbance) supersonic wind tunnel for the NASA-Ames Fluid Mechanics Laboratory (FML).

This change is a result of the need to bring the full-scale tunnel on-line as rapidly as possible to impact the NASA High Speed Research Program (HSRP). The development of a cryogenic adaptive nozzle and other sophisticated features of the tunnel will now happen later.

The following are the objectives in support of the new Fluid Mechanic Laboratory (FML) quiet supersonic wind tunnel: (I) Develop a unique injector drive system using the existing FML indraft compressor; (2) Develop an FML instrumentation capability for quiet supersonic wind tunnel evaluation and transition studies at NASA-Ames; (3) Determine the State of the Art in quiet supersonic wind tunnel design; (4) Author: Stephen W.

Wolf. Required^ research in these areas determines flTe Ihaximum design Reynolds numbers* for a quiet tunnel. Experimental data for current techniques to control and reduce noise J^| ygl| in supersonic and hypersonic wind tu nneir by laminarization of nozzle wall boundary layers and by noise radiation shields.

The main emphasis is to bring on-line a full-scale Mach tunnel as rapidly as possible to impact the NASA High Speed Research Program (HSRP). The development of a cryogenic adaptive nozzle and other sophisticated features of the tunnel will now happen later, after the Author: Stephen W.

Wolf. Aspects of the design and construction of the Laminar Flow Supersonic Wind Tunnel at the NASA-Ames Fluid Mechanics Laboratory are discussed. The wind tunnel is. The main objective of this work was the development of an interim quiet (low-disturbance) supersonic wind tunnel for the NASA-Ames Fluid Mechanics Laboratory (FML).

This is a result of the need to bring the full-scale tunnel on-line as rapidly as possible to impact the NASA High Speed Research Program (HSRP).Author: Stephen W. Wolf. Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle.

By Stephen W. Wolf. Abstract. Aspects of the design and construction of the Laminar Flow Supersonic Wind Tunnel at the NASA-Ames Fluid Mechanics Laboratory are discussed. The wind tunnel is to be used as part of the NASA High Speed Research Program (HSRP) Author: Stephen W. Wolf. The main objectives of this work is to demonstrate the potential of a cryogenic adaptive nozzle to generate quiet (low disturbance) supersonic flow.

A drive system was researched for the Fluid Mechanics Laboratory (FML) Laminar Flow Supersonic Wind Tunnel (LFSWT) using a pilot : Stephen D.

Wolf. Lockheed Martin X QueSST. The Lockheed Martin X QueSST ("Quiet Supersonic Transport") is an American experimental supersonic aircraft being developed for NASA's Low-Boom Flight Demonstrator program.

Preliminary design started in Februarywith the X scheduled for delivery in late for flight tests from Built by: Lockheed Martin. An experiment was performed in the Mach ``quiet" tunnel at the NASA Langley Research Center to document the linear and nonlinear development of pairs of oblique waves over a 7^rc half-angle cone.

Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle. San Jose, CA, MCAT Institute. TURABIAN. Wolf, Stephen W. Development of a Quiet Supersonic Wind Tunnel with a Cryogenic Adaptive Nozzle.

San Jose, CA: MCAT Institute, Get this from a library. Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle. [Stephen W D Wolf; United States. National Aeronautics and Space Administration.]. The hypersonic quiet nozzle has to be carefully designed by the aerodynamic techniques to obtain the quiet-flow test region with low noise levels comparable to flight.

Two conceptual aerodynamic techniques tolaminarizethe nozzle wall boundary layer in the past quiet nozzle design, such as the use of the slower expansion nozzle and the bleed Author: Ruiqu Li, Junmou Shen, Jian Gong.

Get this from a library. Development of a quiet supersonic wind tunnel with a cryogenic adaptive nozzle: final report. [Stephen W D Wolf; United States. National Aeronautics and Space Administration.]. The goal of wind tunnel design is to generate a uniform air flow with minimum turbulence intensity and low flow angle.

The nozzle is the main component of wind tunnels to create a uniform flow with minimal turbulence. Pressure distribution along nozzle walls directly affects the boundary layer thickness, pressure losses and non-uniformity of flow velocity through the test by: 2.

To solve these problems, MHI Group has engaged in the research and development of cryogenic wind tunnels which lowers the temperature of the airflows to bring the Reynolds number of the measurement closer to the actual machine test, and supersonic, quiet nozzles which can.

TOP BOOKS Development of a Quiet Supersonic Wind Tunnel with a Cryogenic Adaptive Nozzle A VI Vorderer Orient. Giftschlangen: 1: 18 Mio.

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A new tandem nozzle supersonic wind tunnel was designed for Technische Universität Braunschweig. Based on the infrastructure of the existing M = 6 Ludwieg tube in Braunschweig (HLB), two nozzles.

A description of a supersonic protractor is included in conjunction with a discussion of its application to nozzle eunalysis and design. IKTRODUCTIOir One of the major problems in the design of a supersonic wind tunnel is the determination of the contours of the svrpersonic nozzle so that parallel n-riri unifoirm flow in the test section may he.

Development of Quiet-Flow Supersonic Wind Tunnels for Laminar-Turbulent Transition Research: Final Report easy to use quiet-nozzle design system from the several separate codes Development of square nozzles for high-speed, low-disturbance wind tunnels.

Master’s thesis, School of Aeronautics and Astro-File Size: KB.schematic of the Purdue Ludwieg tube in Figure 1. All supersonic wind tunnels known to the author are designed specifically with this geometry.

Transonic wind tunnels, however, can be designed in a few other ways than a supersonic wind tunnel. They could have two throats, one downstream and one upstream of the test section, or one throat,Author: Shin Matsumura.As part of earlier work aimed at development of supersonic quiet wind tunnels with axisymmetric or 2D cross-sections, the author adapted and used the Sivells wind tunnel nozzle design code (J.C.

Sivells, AEDC-TR, ) and the Harris boundary layer code (Harris and Blanchard, NASAFile Size: 1MB.