3 edition of Development of quiet-flow supersonic wind tunnels for laminar-turbulent transition research found in the catalog.
Development of quiet-flow supersonic wind tunnels for laminar-turbulent transition research
Steven P. Schneider
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va
Written in English
|Other titles||Development of quiet flow supersonic ...|
|Statement||Steven P. Schneider.|
|Series||NASA contractor report -- NASA CR-197286.|
|Contributions||United States. National Aeronautics and Space Administration.|
|The Physical Object|
Typical applications in wind-tunnel experiments are the localization of the laminar–turbulent transition and the identification of laminar or turbulent flow separations [26,27]. In addition, the measurement method was transferred to the free field to localize the laminar–turbulent transition on aircraft wings [ 28 ] and helicopter rotors Author: Torben Reichstein, Alois Peter Schaffarczyk, Christoph Dollinger, Nicolas Balaresque, Erich Schülein. The development of turbulent spots in a hypersonic boundary layer was studied on the nozzle wall of the Boeing/AFOSR Mach-6 Quiet Tunnel. Under quiet flow conditions, the nozzle wall boundary layer remains laminar and grows very thick over the long nozzle length.
The subject of laminar-turbulent transition is of considerable practical importance and has a wide range of engineering applications. For this reason, the International Union of Applied Mechanics decided to sponsor a third Symposium on "Laminar-Turbulent Transition", which would be organised by the ONERA Toulouse Research Center and held at "Ecole Nationale Superieure de l'Aeronautique et de l. Laminar-turbulent transition in boundary layers is a critical factor in the design of hypersonic vehicles, because of its impact on overall aerodynamic and heat transfer characteristics. Numerical and experimental studies have demonstrated that the modal growth of planar Mack modes is responsible for laminar-turbulent transition on sharp cones.
Feb 13, · However, the tunnel can only produce a noisy flow, meaning that the velocity and pressure of the air flow fluctuate. The Office of Naval Research grant is funding a nozzle that enables the tunnel to produce quiet flow, which more closely approximates what occurs with flight in Earth's atmosphere. As the air flows through the experimental area of a wind tunnel, it flows across the tunnel's interior wall, where it also experiences laminar-turbulent transition, Schneider explains. Consequently, as the tunnel size or pressure inside the tunnel increase, it becomes increasingly difficult to maintain a quiet flow.
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This grant supported r_search into quiet-flow supersonic wind-tunnels, between May and December Quiet-flow nozzles operate with laminar nozzle-wall boundary layers, in order to provide low-disturbance flow for studies of laminar- turbulent transition under conditions comparable to.
Development of Quiet-Flow Supersonic Wind Tunnels for Laminar-Turbulent Transition Research: Final Report for NASA Langley Grant NAG Steven P. Schneider Assistant Professor of Aerodynamics School of Aeronautical and Astronautical Engineering Purdue University West Lafayette, IN Abstract.
This grant supported research into quiet-flow supersonic wind-tunnels, be-tween February and February Quiet-flow nozzles operate with lam-inar nozzle-wall boundary layers, in order to provide low-disturbance flow for studies of laminar-turbulent. Get this from a library.
Development of quiet-flow supersonic wind tunnels for laminar-turbulent transition research: final report. [Steven P Schneider; United States.
National Aeronautics and. This grant supported research into quiet-flow supersonic wind-tunnels, between February and February Quiet-flow nozzles operate with laminar nozzle-wall boundary layers, in order to provide low-disturbance flow for studies of laminar-turbulent transition under conditions comparable to Author: Steven P.
Schneider. This grant supported research into quiet-flow supersonic wind-tunnels, between May and December Quiet-flow nozzles operate with laminar nozzle-wall boundary layers, in order to provide low-disturbance flow for studies of laminar-turbulent transition under conditions comparable to makethemworkforyou.com: Steven P.
Schneider. Development of Quiet-Flow Supersonic Wind Tunnels for Laminar-Turbulent Transition Research: Final Report for NASA Langley Grant NAG 5a.
CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM ELEMENT NUMBER 6. AUTHOR(S) 5d. PROJECT NUMBER 5e. TASK NUMBER 5f. WORK UNIT NUMBER 7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES). The Development of Hypersonic Quiet Tunnels. A review on the development of quiet-low hypersonic wind tunnels with low noise levels comparable to light is presented.
The team from NASA Langley Research Center led by Ivan Beckwith spent over three decades developing the first supersonic and hypersonic quiet makethemworkforyou.com: Steven P. Schneider. A high-Reynolds number Mach-6 quiet-flow Ludwieg tube is being developed at Purdue, to enable affordable low-noise hypersonic transition research.
The design and fabrication of this facility is reviewed. The facility will use instrumentation developed in the low-Reynolds number Mach-4 quiet-flow Ludwieg tube; this instrumentation is also makethemworkforyou.com by: 3.
LAMINAR-TURBULENT TRANSITION CORRELATIONS IN SUPERSONIC / HYPERSONIC FLAT PLATE FLOW G.A. Simeonides* *Hellenic Aerospace Industry, P.O. Box 23, GR Schimatari, Greece various wind tunnels, has been previously assembled in a database, and elaborated to LAMINAR-TURBULENT TRANSITION CORRELATIONS 2 Data Correlation and Regression Analysis.
A controlled, laser-generated perturbation was created in the freestream of the Boeing/U.S. Air Force Office of Scientific Research Mach 6 Quiet Tunnel.
The freestream perturbation convected downstream in the wind tunnel to interact with a flared cone model. The model is a body of revolution bounded by a circular arc with a m makethemworkforyou.com by: 4. Oct 13, · The paper is devoted to an experimental study of laminar-turbulent transition in a three-dimensional supersonic boundary layer.
The experiments were conducted at the low nose supersonic wind tunnel T of ITAM at Mach numbers M=2 - 4. Model is a symmetrical wing with a 45° sweep angle, a 3 percent-thick circular-arc makethemworkforyou.com by: 2.
This paper presents the design and the results of the qualification test campaign of a multiple Mach number supersonic wind tunnel designed for induced boundary layer transition. In the context of National EXperimental Supersonic Transport program (NEXST), JAXA developed an optimized supersonic high swept wing presenting an extending laminar region, namely a supersonic natural laminar flow wing in  and conducted some wind tunnel Cited by: 6.
Aug 30, · Laminar-turbulent transition research in the Purdue Mach-4 Quiet-Flow Ludwieg Tube. Development of the NASA-Ames Low-Disturbance Supersonic Wind Tunnel for transition studies at Mach Development of a Mach 18 quiet helium tunnel for transition makethemworkforyou.com by: In fact, most of the time, for hypersonic applications, one builds blow-down wind tunnels.
The wind tunnels for lower Mach number are usually continuous wind tunnels, able to work during several hours. At the opposite, a blow-down wind tunnel operates for a Cited by: 1. Get this from a library. Supersonic quiet-tunnel development for laminar-turbulent transition research: final report for NASA Langley grant NAG [Steven P Schneider; United States.
National Aeronautics and Space Administration.]. laminar-turbulent transition is summarized in , including a tabulation of the data of [17,18] in the well known plot of transition Reynolds number on “sharp” cones in wind tunnels and flight versus Mach number, Fig.
4 . The excessive data scatter in Fig. 4 has been explained in [20,24] with the help of. Nov 22, · Bottini H., Paniagua G., Schreivogel P., Sonda A., de las Heras S., Design and qualification of a supersonic wind tunnel for induced boundary layer transition research. Proceedings of the Institution of Mechanical Engineers, Part G: Journal Author: Henny Bottini, Bayindir H.
Saracoglu, Guillermo Paniagua. Laminar-to-Turbulent Stability and Transition Helen L. Reed Professor Aerospace Engineering Texas A&M University Support: AFOSR, AFRL, NASA Langley, NASA Dryden, Lockheed Martin AFOSR/NASA National Center for Hypersonic Research in Laminar-Turbulent Transition TAMU Supercomputer Center Pointwise, Aerosoft 1.
May 07, · Since the s, various types of research on hypersonic quiet wind tunnels have been carried out in China (while pioneering research has been carried out abroad since the s). Zhou and Chang were the first researchers in China to study quiet-flow wind tunnels.
They began theoretical and experimental research on hypersonic quiet wind Cited by: 1.The state of the boundary layer, laminar or turbulent, strongly influences the thermal state of the surface, in particular if the surface is radiation cooled. The thermal state governs thermal Author: Ernst Heinrich Hirschel.May 06, · The bleed slot is necessary for the requirement of the hypersonic quiet flow all over the world.
The aim of the bleed slot is to decrease the influence of the disturbances from the contraction of the quiet nozzle to the boundary layer downstream of the throat, so that the boundary layer of the nozzle could be maintained as laminar flow.
The main parameters of the bleed slot include the Cited by: 1.