54 research outputs found
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Decay of the supersonic turbulent wakes from micro-ramps
The wakes resulting from micro-ramps immersed in a supersonic turbulent boundary layer at Ma = 2.0 are investigated by means of particle image velocimetry. Two micro-ramps are investigated with height of 60% and 80% of the undisturbed boundary layer, respectively. The measurement domain is placed at the symmetry plane of the ramp and encompasses the range from 10 to 32 ramp heights downstream of the ramp. The decay of the flow field properties is evaluated in terms of time-averaged and root-mean-square (RMS) statistics. In the time-averaged flow field, the recovery from the imparted momentum deficit and the decay of upwash motion are analyzed. The RMS fluctuations of the velocity components exhibit strong anisotropy at the most upstream location and develop into a more isotropic regime downstream. The self-similarity properties of velocity components and fluctuation components along wall-normal direction are followed. The investigation of the unsteady large scale motion is carried out by means of snapshot analysis and by a statistical approach based on the spatial auto-correlation function. The Kelvin-Helmholtz (K-H) instability at the upper shear layer is observed to develop further with the onset of vortex pairing. The average distance between vortices is statistically estimated using the spatial auto-correlation. A marked transition with the wavelength increase is observed across the pairing regime. The K-H instability, initially observed only at the upper shear layer also begins to appear in the lower shear layer as soon as the wake is elevated sufficiently off the wall. The auto-correlation statistics confirm the coherence of counter-rotating vortices from the upper and lower sides, indicating the formation of vortex rings downstream of the pairing region
Density Field Reconstruction of an Overexpanded Supersonic Jet using Tomographic Background-Oriented Schlieren
A Tomographic Background-Oriented Schlieren (TBOS) technique is developed to
aid in the visualization of compressible flows. An experimental setup was
devised around a sub-scale rocket nozzle, in which four cameras were set up in
a circular configuration with 30{\deg} angular spacing in azimuth. Measurements
were taken of the overexpanded supersonic jet plume at various nozzle pressure
ratios (NPR), corresponding to different flow regimes during the start-up and
shut-down of rocket nozzles. Measurements were also performed for different
camera parameters using different exposure times and f-stops in order to study
the effect of measurement accuracy. Density gradients and subsequently
two-dimensional line-of-sight integrated density fields for each of the camera
projections are recovered from the index of refraction field by solving a
Poisson equation. The results of this stage are then used to reconstruct
two-dimensional slices of the (time-averaged) density field using a tomographic
reconstruction algorithm employing the filtered back-projection and the
simultaneous algebraic reconstruction technique. By stacking these
two-dimensional slices, the (quasi-) three-dimensional density field is
obtained. The accuracy of the implemented method with a relatively low number
of sparse cameras is briefly assessed and basic flow features are extracted
such as the shock spacing in the overexpanded jet plume
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Numerical and experimental investigations of the supersonic microramp wake
The flow past a microramp immersed in a supersonic turbulent boundary layer is studied by means of numerical simulations with the implicit large-eddy simulation technique and experiments conducted with tomographic particle image velocimetry. The experimental data are mostly used to verify the validity of the numerical results by ample comparisons on the time-averaged velocity, turbulent statistics, and vortex intensity. Although some discrepancies are observed on the intensity of the upwash motion generated by the streamwise vortex pair, the rates of the recovery of momentum deficit and the decay of streamwise vortex pair intensity are found in good agreement. The instantaneous flow organization is inspected, making use of the flow realizations available from implicit large-eddy simulation. The flow behind the microramp exhibits significant large-scale unsteady fluctuations. Notably, the quasi-conical shear layer enclosing the wake is strongly undulated under the action of Kelvin–Helmholtz (K–H) vortices. The resulted vortices induce localized high-speed arches in the outer region and a deceleration within the wake associated with ejection of low-momentum fluid. Because of the presence of the K–H vortex, the streamwise vortex filaments exhibit downward and outward motions. The further evolution of vortical structures within the wake features the development of K–H vortices from arch shape to full ring in the far wake, under the effects of the streamwise vortices, which induce an inward motion of the vortex legs and eventually connect the vortex at the bottom
An experimental realisation of steady spanwise forcing for turbulent drag reduction
We present an experimental realisation of spatial spanwise forcing in a
turbulent boundary layer flow, aimed at reducing the frictional drag. The
forcing is achieved by a series of spanwise running belts, running in
alternating spanwise direction, thereby generating a steady spatial square-wave
forcing. Stereoscopic particle image velocimetry is used to investigate the
impact of actuation on the flow in terms of turbulence statistics, performance
characteristics, and spanwise velocity profiles, for a waveform of . An extension of the classical spatial Stokes layer theory is proposed
based on the linear superposition of Fourier modes to describe the
non-sinusoidal boundary condition. The experimentally obtained spanwise
profiles show good agreement with the extended theoretical model. In line with
reported numerical studies, we confirm that a significant flow control effect
can be realised with this type of forcing. The results reveal a maximum drag
reduction of 26% and a maximum net power savings of 8%. In view of the limited
spatial extent of the actuation surface in the current setup, the drag
reduction is expected to increase further as a result of its streamwise
transient. The second-order turbulence statistics are attenuated up to a
wall-normal height of , with a maximum streamwise stress
reduction of 44% and a reduction of integral turbulence kinetic energy
production of 39%
Surface pressure and aerodynamic loads determination of a transonic airfoil based on particle image velocimetry
Wp-2 basic investigation of transition effect
An important goal of the TFAST project was to study the effect of the location of transition in relation to the shock wave on the separation size, shock structure and unsteadiness of the interaction area. Boundary layer tripping (by wire or roughness) and flow control devices (Vortex Generators and cold plasma) were used for boundary layer transition induction. As flow control devices were used here in the laminar boundary layer for the first time, their effectiveness in transition induction was an important outcome. It was intended to determine in what way the application of these techniques induces transition. These methods should have a significantly different effect on boundary layer receptivity, i.e. the transition location. Apart from an improved understanding of operation control methods, the main objective was to localize the transition as far downstream as possible while ensuring a turbulent character of interaction. The final objective, involving all the partners, was to build a physical model of transition control devices. Establishing of such model would simplify the numerical approach to flow cases using such devices. This undertaking has strong support from the industry, which wants to include these control devices in the design process. Unfortunately only one method of streamwise vortices was developed and investigated in the presented study
Particle image velocimetry measurements of a shock wave/turbulent boundary layer interaction
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