The Development and Application of Optical Measurement Techniques for High Reynolds Number Testing in Cryogenic Environment

Germain, Eric; Quest, Jürgen

doi:10.2514/6.2005-458

Cited by 17 publications

(4 citation statements)

References 4 publications

(4 reference statements)

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“…Loose et al (2000) and Alhaj and Seume (2010), for example, used a combined PIV and BOS investigation for the investigation of wake flows in linear turbine cascade facilities. Challenging wind tunnel applications under cryogenic conditions have been reported by Germain and Quest (2005), Loose et al (2006), andFey et al (2010). Combustion research can take advantage of the ability of BOS to visualize and measure heat plumes and flames (Iffa et al 2011), but also to determine concentration levels of different fuel sprays (Bang and Lee 2013; Lee et al 2011Lee et al , 2013Tillmann et al 2014) or gas jets as performed by Iffa et al (2010), Ducasse et al (2010) and Veser et al (2011).…”

Section: Bos Applications In Complex Facilitiesmentioning

confidence: 99%

Background-oriented schlieren (BOS) techniques

2015

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Section: Bos Applications In Complex Facilitiesmentioning

confidence: 99%

Background-oriented schlieren (BOS) techniques

2015

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“…The measurement technique is the stereo pattern tracking described in Ref. 19. The wing twist and bending is derived from the movement of markers in space and recorded by a stereo camera system.…”

Section: Measurementsmentioning

confidence: 99%

Downward pointing winglet design and assessment within the M-DAW research project

Hantrais-Gervois¹,

Grenon²,

Mann³

et al. 2009

Aeronaut. j.

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The design and performance analysis of a wing tip device proposed within the M-DAW project by ONERA is presented. A proto-design process is described and the device was thoroughly assessed (mainly with Reynolds-Averaged Navier-Stokes simulations). The process was further explained through wind-tunnel tests at both low speed and high speed in the pressurised and cryogenic European transonic wind tunnel in Cologne. The device is a downward pointing winglet designed for a retrofit scenario (the wing could be modified only within the 96% – 100% bounds of the span). It was designed to keep the wing root bending moment of the clean wing at cruise unchanged so that the aerodynamic gains are the net gains provided by the device that can be directly installed without structural modifications of the wing.

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“…The mechanism of Reynolds number scaling effects on aerodynamic characteristics was not analyzed. Several RANS solvers, such as object-oriented software elsA of ONERA and unstructured RANS Solver TAU from DLR were developed for accurately predicting lift, drag, and moments of transports aircraft [29,30]. However, most previous CFD studies focused on how to improve the predicting accuracy of aerodynamic properties of transport aircraft.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Reynolds Number Effects on Aerodynamic Characteristics of a Transport Aircraft

et al. 2021

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The scale difference between the real flight vehicle and the experimental model results in the Reynolds number effect, which makes it unreliable to predict the aerodynamic characteristics of flight vehicles by wind tunnel testing. To understand the mechanism of Reynolds number effects on the aerodynamic characteristics of the supercritical wing that is commonly used in transport aircraft in more detail, surface pressure wind tunnel tests of a transport aircraft reference model with a wing-body configuration were conducted in the European Transonic Windtunnel (ETW) at different Reynolds numbers. There are 495 pressure taps in total equipped on the surface of the test model with the Mach numbers ranging from 0.6 to 0.86 and Reynolds number varying from 3.3 × 106 to 35 × 106. In addition, an in-house developed CFD tool that has been validated by extensive experimental data was used to correct the wing deformation effect of the test model and achieve detailed flow structures. The results show that the Reynolds number has a significant impact on the boundary layer displacement thickness, surface pressure distribution, shock wave position, and overall aerodynamic force coefficients of the transport aircraft in the presence of shock wave and the induced boundary layer separation. The wind tunnel data combined with flow fields achieved from CFD show that the essence of the Reynolds number effect on the aerodynamic characteristics of transport aircraft is the difference of boundary layer development, shock wave/boundary layer interaction, and induced flow separation at different Reynolds numbers.

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The Development and Application of Optical Measurement Techniques for High Reynolds Number Testing in Cryogenic Environment

Cited by 17 publications

References 4 publications

Background-oriented schlieren (BOS) techniques

Background-oriented schlieren (BOS) techniques

Downward pointing winglet design and assessment within the M-DAW research project

Investigation of Reynolds Number Effects on Aerodynamic Characteristics of a Transport Aircraft

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