2 edition of Evaluation of flow quality in two large NASA wind tunnels at transonic speeds found in the catalog.
Evaluation of flow quality in two large NASA wind tunnels at transonic speeds
by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service] in Washington, D.C, [Springfield, Va
Written in English
|Statement||William D. Harvey, P. Calvin Stainback, and F. Kevin Owen|
|Series||NASA technical paper -- 1737|
|Contributions||Stainback, P. Calvin, Owen, F. Kevin, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center|
|The Physical Object|
|Pagination||73 p. :|
|Number of Pages||73|
Subsonic tunnel. Low-speed wind tunnels are used for operations at very low Mach number, with speeds in the test section up to km/h (~ m/s, M = ) (Barlow, Rae, Pope; ). They may be of open-return type (also known as the Eiffel type, see figure), or closed-return flow (also known as the Prandtl type, see figure) with air moved by a propulsion system usually consisting of large. Flow unsteadiness and model vibration in the RAE 3ft x 3ft tunnel have Impeded static and dynamic measurements at subsonic and transonic speeds. The unsteadiness was measured with pressure transducers both in the 3ft x 3ft tunnel and a l/9 scale model of this tunnel .
This paper concerns one of the NASA in-house activities, the Langley Laminar Flow Control (LFC) Project, which was carried out in the Langley 8-foot Transonic Pressure Tunnel (8-ft TPT). The idea for such an undertaking came from Dr. Werner Pfenninger in and stemmed, primarily, from a desire to know more about the compatability of a high Cited by: 3. Transonic flow occurs when there is mixed sub- and supersonic local flow in the same flowfield (typically with freestream Mach numbers from M = or to ). Usually the supersonic region of the flow is terminated by a shock wave, allowing the flow to slow down to subsonic speeds. This complicates both computations and wind tunnel Size: 2MB.
Impact of Flow Quality in Transonic Cascade Wind Tunnels: Measurements in an HP Turbine Cascade in inlet boundary layer thickness had no effect on the downstream midspan losses and the sec-ondary losses. A value of for the axial-velocity-density ratio (AVDR) is a necessary but not sufﬁ-cient condition for two-dimensional ﬂow at the. Design and Analysis of Transonic Wind Tunnel By T. Kumaraswamy, V. V. S. Nikhil Bharadwaj & Parthasarathy Garre MLRIT, India. Abstract- The Transonic Wind Tunnel is used to test aircraft models at speeds from Mach number to Transonic flows consist of mixed subsonic and supersonic flow File Size: KB.
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NASA Technical Paper Evaluation of Flow Quality in Two Large NASA Wind Tunnels at Transonic Speeds William D.
Harvey, P. Calvin Stainback, and F. Kevin Owen DECEMBER I File Size: 2MB. Evaluation of flow quality in two large NASA wind tunnels at transonic speeds Article (PDF Available) January with 39 Reads How we measure 'reads'. Experimental results are presented of an extensive and systematic flow quality study of the settling chamber, test section, and diffuser in the Langley 8 foot transonic pressure tunnel and the Ames 12 foot pressure wind tunnel.
Get this from a library. Evaluation of flow quality in two large NASA wind tunnels at transonic speeds. [Bill Harvey; P Calvin Stainback; F Kevin Owen; United States.
National Aeronautics and Space Administration. Scientific and Technical Information Branch.; Langley Research Center.]. Evaluation of flow quality in two large NASA wind tunnels at transonic speeds. detailed flow quality measurements were made in two prospective NASA wind tunnels.
Experimental results are presented of an extensive and systematic flow quality study of the settling chamber, test section, and diffuser in the Langley 8 foot transonic pressure Author: P. Stainback, W. Harvey and F. Owen. an evaluation in a modern wind tunnel of the transonic adaptive wall adjustment strategy developed by npl in the 's m.
lewis the university of southampton southampton, england grant nsg february [u&sa-cr) by evaluatiop iu a mouerbi r 17 uiud tubnel of the transonic adaptive hall.
One of the inherent difficulties in utilizing a ventilated test section wind tunnel is the interaction of the model flow field and the test section walls. If high quality aerodynamic data is required for the system under test it is necessary to determine the impact of the test section walls on the flow field around the model.
A parametric study was undertaken using the CFD code USM3Dns to Cited by: 1. Once satisfactory results regarding the flow quality requirements in the test section under various conditions were achieved, a 2D model, NACAand a 3D standard model for the transonic wind tunnels, AGARD-B, are manufactured and tested under various conditions for the purpose of integral calibration and validation of the tunnel by: 6.
Some of the earl iest experimental results at transonic speeds were obtained by the wing-flow method. The location of a small model in a region of i ncreased airspeed over the curved upper surface of the air plane wing allowed the model to be tested at transonic speeds when the aircraft was dived at high subsonic speeds.
This approach has been used in the RAE 4-ft×3-ft wind tunnel, the NASA Ames ft transonic wind tunnel, and the National Transonic Wind Tunnel at NASA Langley.
Unfortunately, these sudden expansions can create large-scale unsteady flows associated with flow separation, which produce mean gradients in the flow upstream of the by: Measurement and assessment of wind tunnel flow quality Article (PDF Available) in Progress in Aerospace Sciences 44(5) July with 2, Reads How we measure 'reads'.
Evaluation of flow quality in two NASA transonic wind tunnels. By P. Stainback, F. Owen and W. Harvey. Abstract. Tests have been conducted in the Langley Research Center 8-foot Transonic Pressure Tunnel and the Ames Research Center foot pressure wind tunnel in order to measure characteristic disturbance levels and energy spectra in Author: P.
Stainback, F. Owen and W. Harvey. I have previously covered some of the analysis used to design the throat section of the wind tunnel, this time I shall cover some of the design used for the rest of the tunnel design.
The idea was to use a pressure vessel coupled to a large diameter ball valve, so that large volumes of. Photograph to right is the National Transonic Facility which is one of 23 major wind tunnels at NASA's Langley Research Center.
NASA's Lewis Research Center is know for its studies and innovations in aircraft propulsion systems. Wind Tunnel All tests were performed in a wind tunnel with a test section of (60cm (W) * 60cm (H) * cm (L)).
The tunnel is of open circuit suction type. Two engines that eject their exhaust gases downstream of the test section through ejector systems supply the main circuit power of the tunnel.
Side suction is supplied by a smaller engine. wind tunnels, and of the need to provide guidance for the designer of new facilities, a Conveners Group was formed by the AGARD FDP (members are listed in the Appendix) with the objective of specifying, for subsonic and transonic speeds, data-accuracy and flow-quality.
The by foot Transonic Wind Tunnel (foot TWT) Facility is part of the Unitary Plan Wind Tunnel (UPWT) complex at NASA's Ames Research Center at Moffett Field, California, where generations of commercial and military aircraft and NASA space vehicles, including the space shuttle, have been designed and tested.
The European Transonic Wind Tunnel (ETW) is similar to the National Transonic Facility, a pressurized cryogenic, closed circuit, continuous-flow, fan-driven wind tunnel. It can be operated in closed and slotted wall configurations for testing full and half-models from Mach numbers of up to light supersonic conditions at M ∞ = An evaluation of the free stream flow quality associated with a Laminar Flow Control experiment was carried out in the Langley Research Center 8-Foot Transonic Pressure Tunnel (8' TPT).
The facility was modified with turbulence manipulators and a liner that provided a flow field around a yawed super-critical airfoil that is conducive to transition by: 3.
Transonic Aerodynamics Wind Tunnel Testing Considerations W.H. Mason The Large Second Generation of Cryogenic Tunnels Dennis E. Fuller, Guide for Users of the National Transonic Facility, NASA TMJuly Michael J.
Goodyer, The Cryogenic Wind Tunnel, File Size: 3MB. The Foot Transonic Dynamics Tunnel (TDT) was not always ft. When constructed inthe tunnel was known as the Foot Pressure Tunnel. The tunnel was made form approximately 5, tons of steel.
An 8,horsepower electric motor and a Center: Langley Research Center. Testing this new design in the Foot HST, Langley engineers found that it allowed for transonic speeds (up to and beyond the speed of sound, Mach 1, approximately mph at sea level).
Retrofitted with a new slotted test section throat and re-powered to 60, hp, the facility was re-designated the Foot Transonic Tunnel (TT) in December Center: Langley Research Center.Using compressed air, AEROLAB Transonic Wind Tunnels offer running speeds of M= to M= Employing variable test section porosity, computer-controlled valves, chokes and flaps, target airspeeds are easy to achieve and maintain.
Systems with test section sizes of 8-inch x 8-inch (cm x cm) and inch x inch (51cm x 51cm) are available. Performance Specifications [ ].