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Sunday, May 3, 2020 | History

2 edition of investigation of wind tunnel wall effects at high Mach numbers found in the catalog.

investigation of wind tunnel wall effects at high Mach numbers

John K. Leydon

investigation of wind tunnel wall effects at high Mach numbers

by John K. Leydon

  • 126 Want to read
  • 6 Currently reading

Published in Pasadena .
Written in English

    Subjects:
  • Wind tunnels.

  • Edition Notes

    Statementby John K. Leydon and Walter B. Miller.
    ContributionsMiller, Walter Bernard, 1918- joint author.
    Classifications
    LC ClassificationsTL567.W5 L4
    The Physical Object
    Pagination1 v. (various pagings)
    ID Numbers
    Open LibraryOL6076064M
    LC Control Number50020903
    OCLC/WorldCa3916047

    The investigated compressor cascade called V– was designed for the hub section of a stator blade in a highly loaded axial compressor (Hoheisel ).The design conditions with an inlet Mach number of Ma 1 = and an inlet flow angle of β 1 = ° lead to a fully subsonic cascade flow. The Reynolds number based on blade chord length of Re 1 = causes boundary layer transition Author: L. Hilgenfeld, L. Fottner. WIND TUNNEL INVESTIGATION OF FLOWFIELD ON THE FOWLER FLAP AND IN THE COVE USIND PIV METHOD Fig. 5. The Airfoil Model in the Wind Tunnel Fig. 6. Detail of the Laser Sheet 4 Experimental Results All tests were performed at the Reynolds number and Mach number The data were processed with all standard wind.

    The ramjet engine is mounted to the exit nozzle of the Supersonic Wind Tunnel (SSWT). The duct area dimensions of the ramjet engine are inches wide by inches high to match the exit nozzle of the Super Sonic Wind Tunnel. The overall length of the ramjet engine is six feet long. The length is broken into three equal. work ofLudwig Mach of Vienna in 's indraft wind tunnel had a cross-sectionof x mm and was driven by a centrifugal fan that could produce a speed of10 m/sec. Wire mesh over the inletstraightened the flow. One side ofthe test section was glass and the others were black on the inside. The flow was observed photographedFile Size: KB.

      The model was instrumented with a temperature-sensitive paint to measure globally and non-intrusively the surface temperature and thus the boundary-layer transition. A marked influence of a variation in the wall temperature ratio on transition was observed for all considered Mach numbers, being this effect more pronounced at lower Mach : Marco Costantini, Steffen Risius, Christian Klein. The tunnel is equipped with three complete nozzle chambers which presently are fitted with the nozzles for the Mach numbers , , and Supersonic Wind Tunnel. a) Side view, b) Top view.


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Investigation of wind tunnel wall effects at high Mach numbers by John K. Leydon Download PDF EPUB FB2

Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers From to Terry J. Larson Analytical Mechanics Associates, Hampton, Virginia Timothy R. Moes Ames Research Center, Dryden Flight Research Facility, Edwards, California Paul M.

Siemers III Langley Research Center, Hampton, Virginia w I_I/LSA National Aeronautics andFile Size: 1MB. Numerical Investigation of Wind Tunnel all Effects on a Supersonic Finned Missile Loai A. Elmahdy*, M.Y.M Ahmed*, O.K. Mahmoud* and O.E. Abdel Hamid* Abstract: One major aspect of wind tunnel measurements is the influence of test section walls on the measured data.

In this paper, a numerical investigation of the supersonic flow. This wind tunnel and aeroacoustics (S2A) reaches a velocity of km/h in a test section of 24 m 2, allowing one to study aerodynamics and acoustics on vehicles at scale 1 (see Fig.

14). For the simulation of the ground effects, this wind tunnel is equipped with a central moving carpet under the vehicle, which rolls at the same wind tunnel Cited by: 2.

Report presenting a method for the design of supersonic-wind-tunnel nozzles that produce uniform flow over a continuously variable Mach number range without the use of flexible walls.

Experimental results from a preliminary investigation of the tunnel are included, including calibration survey of flow, Mach number distributions, and pressure gradients are by: 2.

"Results are presented for a wind-tunnel investigation of an airplane model with a percent-thick unswept wing of aspect ratio at Mach numbers from to at a Reynolds number of million.

Longitudinal characteristics are presented for the basic model and for configuration variations involving two types of wing camber, an area-rule fuselage modification, various external-store Author: James L. Summers, Stuart L.

Treon, Lawrence A. Graham. WIND-TUNNEL INVESTIGATION OF TRE STATIC AERODYNAMIC CHARACTERISTICS OF AN FOOT (METER) ALL-FLl3XIBI.X PARAWING By Charles E. Libbey, George M. Ware, and Rodger L. Naeseth Langley Research Center SUMMARY An investigation has been conducted in the Langley full-scale tunnel to determine the performance and the static stability and control characteristicsFile Size: 2MB.

OSBORNE, R. S., High-Speed Wind-Tunnel Investigation of a 1/Scale Model of the D Research Airplane at High Subsonic Mach Numbers and at Mach NACA RM No.

L9C04, Apr. TURNER, L. I., JR., Program for Investigation of Slotted Test Section in Induction Aerodynamics Laboratory Facilities. Memo for CRD Files, Apr.

8, Wind tunnel and CFD investigation of unconventional rigs. The tests were conducted in the NAL m wind tunnel in the Mach number range of to and in the incidence range of -8 deg to 8. Title: Wind-Tunnel Investigation of a Flush Airdata System at Mach Numbers From to Author: Terry J.

Larson, Timothy R. Moes, and Paul M. Siemers III. A high enthalpy wind tunnel is intended to study flow of air around objects moving at speeds much faster than the local speed of sound (hypersonic speeds).

"Enthalpy" is the total energy of a gas stream, composed of internal energy due to temperature, the product of pressure and volume, and the velocity of flow.

Duplication of the conditions of. Tests of humidity effects on flow in a wind tunnel at Mach numbers between and 4 by R.J. Monaghan, M.A. SUMMARY Static and pitot pressure distributions were measured in the -working section of a 5 in.

x 5 in. supersonic wind tunnel at nominal Mach numbers ofand 4, over ranges of absolute humidity at the inlet fromFile Size: 8MB. @article{osti_, title = {An experimental investigation of wall-interference effects for parachutes in closed wind tunnels}, author = {Macha, J M and Buffington, R J}, abstractNote = {A set of 6-ft-diameter ribbon parachutes (geometric porosities of 7%, 15%, and 30%) was tested in various subsonic wind tunnels covering a range of geometric blockages from 2% to 35%.

Static aerodynamic characteristics of experimental nonlifting reentry capsule in combination with rocket booster at Mach numbers from to Development and Performance Investigation of Superso nic Blow-down Wind Tunnel International Journal of Earth Sciences and Engineering ISSNVol. 10, No.

01 SPL, March 20 17, pp. Since the compressibility effects become predominant at \(\mathrm {M\ge \text {}}\), the flow with \(\mathrm {M\,\ge \,\text {}}\) are called high-speed flows and so the wind tunnel is referred to as high-speed wind tunnels.

Further, it is observed that the power required for running a low speed wind tunnel is proportional to cube of test. Wind-tunnel investigation at high subsonic speeds of the effects on static stability characteristics of various modifications to a swept-wing fighter-type airplane model by Goodson, K.

extensive wind tunnel equipment could be saved and reconstructed. Disregarding some slight damages to instruments and the loss of the small experimental tunnel for higher Mach numbers, which burned by indirect action of an air raid on Muenchen, all precious equipment could be used again for further development of the high speed Size: 46KB.

Tunnel-Wall Effect on an Aerofoil at Subsonic Speeds By A. THOM AND LAURA KLANFER Reports and Memoranda No. 2 8 5 I August, 19 51 SummaryThis is a detailed study of the effect of the presence of walls on the flow past a symmetrical aerofoil at zero Size: 1MB.

Even before the advantages of the small-model technique were verified, experimentally and expressed in an NACA report, John Becker, head of the 8-Foot High-Speed Tunnel section, was working to develop a new model support system that would eliminate the interference effects and thus permit wind tunnel testing at higher Mach numbers.

The model under investigation (see Figure 1) is bracketed to the wall of the working section of the wind tunnel or to the wind-tunnel balance. In front of the working section is located the nozzle, which creates a stream of gas with preset and constant cross-sectional velocity, density, and temperature (the alignment grid equalizes the velocity.

Langley's 8-Foot Transonic Pressure Tunnel (TPT) was completed in (on the former site of the Propeller Research Tunnel). The tunnel was capable of operating at pressures between and atmospheres, and had sophisticated air temperature and humidity : Langley Research Center.to 15 × per foot); the Mach number can be varied from to The turbulence level in the test section7 is generally below percent for unit Reynolds number up to 13 × per meter (4 × per foot) at Mach numbers up to The wind tunnel test section is 91 cm (36 in.) wide by cm (90 in.) high.

Hydraulically actuated.NASA's Wind Tunnel Program Office should proceed with the design and development of new subsonic and transonic facilities while conducting the four design trade studies noted in Finding c during the design phase of the wind tunnel program.