On the sensitivity of sound power radiated by aircraft panels to turbulent boundary layer parameters

The objective of the present study is to investigate and quantify how sensitive the response of an aircraft panel is to the change of the turbulent flow parameters. Several empirical models currently exist that provide the turbulent boundary layer wall pressure cross spectrum. These wall pressure cross spectrum models are usually dependent on four parameters: the reference power spectrum, the flow convective velocity, and the coherence lengths in streamwise and spanwise directions. All the proposed models provide different predictions for the wall pressure cross spectrum. Also, real flow conditions over aircraft do not conform to the ideal behavior of the turbulent boundary layer pressure predicted by the models. In this context, the questions that this work aims to explore are “What is the impact of different wall pressure estimates in the radiated sound power?” and “What is the effect of the range of possible flow conditions on the radiated sound power?”. For that objective, data from flight tests and estimates provided by the empirical models are used to predict radiated sound power, and the results are compared. A sensitivity analysis is performed and the relative contribution of each boundary layer parameter to the radiated sound power is obtained.     

An efficient approximation for the vibro-acoustic response of a turbulent boundary layer excited panel

The aim of this study was to present a deterministic model for approximating the vibrations and the acoustic pressure radiated when a thin elastic plate is immersed in a low Mach number flow of fluid. As a prelude to this study, a classical random model based on a wavevector integration technique was used. In the case of a low Mach number turbulent flow, the numerical study showed that the subconvective region of the turbulent excitation power spectrum contributes significantly to the response of the panel. A deterministic approximate model was developed, based on this behaviour of the system.     

大面积高分子压电薄膜水听器对湍流边界层压力起伏的自噪声响应

分析大面积高分子压电薄膜水听器(PVDF)水听器在湍流边界层压力起伏(TBLPF)作用下的电压响应。推导了利用TBLPF的波数频率谱密度和水听器的响应函数来计算TBLPF激励下水听器输出电压的自功率谱密度的一般表达式,并利用转移矩阵法求解了水听器理论模型的响应函数。还计算了该水听器的灵敏度和其对TBLPF响应的等效平面波声压谱密度级。结果表明,大面积PVDF水听器的灵敏度和其对TBLPF的响应谱可能出现弯曲振动谐振峰,这些峰仅靠增加表面覆盖层的厚度是难以抑制的。讨论了避免或抑制这些峰的可能方法。     

Response of unconstrained layer panels to random excitation at a point

The acceleration response of unconstrained layer rectangular panels under random point force excitation has been investigated theoretically and experimentally. In the theory the layer material was assumed to be viscoelastic in nature. Generalized harmonic analysis was used to evaluate the power spectral density and the rms values of acceleration response analytically. The theoretical results are compared with the results obtained from experiments for “all edges simply supported” and “all edges clamped” panel boundary conditions.     

Soft and hard wave excitation on an elastic covering in a turbulent boundary layer

We investigate the nonlinear stage of wave excitation on elastic coverings streamlined by a turbulent boundary layer of incompressible fluid. It has been shown that the traveling wave flutter instability leads to soft wave excitation, while the wave divergence instability defines hard wave excitation.Institute of Applied Physics, Russian Academy of Sciences, Nizhny Novgorod. Translated from Izvestiya Vysshikh Uchebnykh Zavedenii, Radiofizika, Vol. 38, Nos. 3–4, pp. 211–216, March–April, 1995.     

The response of a resonator under a turbulent boundary layer to a high amplitude non-harmonic sound field

A method for finding the acoustic response of a Helmholtz resonator in the wall of a pipe containing fully developed turbulent pipe flow is described, for the case of an intense sound field that can be non-harmonic. The equation of motion for the fluid in the orifice is solved numerically in the time domain, and the orifice resistance is made to vary, during the oscillation cycle, in a way that is governed by the grazing flow parameters and the instantaneous mean flow velocity in the orifice. The mass end correction of the orifice is also allowed to be a function of the grazing flow. Predictions of the cavity pressure variation are presented, for a specified pipe pressure variation, and are compared to measurements; generally good agreement between the two is noted.     

A turbulent data analysis in the Antarctic boundary layer

Summary Data collected by the Institute of Atmospheric Physics of CNR (Italy) during the 1991 Italian Antarctic expedition are used for the development of Earth-air-sea interaction studies. In this paper wind and temperature data obtained by a digitized ultrasonic anemometer-thermometer describe the temporal, statistical and spectral turbulence behaviour in the surface atmospheric boundary layer at different wind conditions and in morphologically different sites. The vertical momentum and thermal fluxes, evaluated through the direct method, are found to be strictly dependent on the local stability condition recorded during the measurements. The examination of the velocities and temperature probability density functions confirms the Lumley and Panofsky hypothesis on the influence of both velocity components on temperature fluctuations. A multichannel spectral analysis confirms the obtained results for the low-frequency range. The authors of this paper have agreed to not receive the proofs for correction.     

Evolution of turbulent kinetic energy in a perturbed turbulent boundary layer

The paper considers the evolution of turbulent kinetic energy in a turbulent boundary layer perturbed by suction. The results show that the boundary layer equilibrium is altered in a non-linear manner due to suppression of the structures near the wall. The behavior, however, suggests that the wavelength of alteration of the equilibrium of the layer is unaffected by a change in Reynolds number and suction rate.     

Implementation of air injection into the turbulent boundary layer of aircraft wing using external pressurized flow

The possibility of using the injection of air into the incompressible turbulent boundary layer of an axisymmetric wing through a finely perforated area provided on the wing surface was studied. The air blowing was implemented via the supply of external pressurized flow through a permeable leading edge of the wing. It is shown that, with the blowing section located on the “flat” side of the wing, only an insignificant reduction in airfoil drag could be achieved. Simultaneously, the data obtained show that there exists a possibility of raising the lift-drag ratio due to a more appropriate choice of blowing-section location in the rarefaction region of the flow.     

Roughness sub-layer investigation of a turbulent boundary layer

Particle image velocimetry (PIV) measurements at relatively low Reynolds numbers in a turbulent boundary layer over a three-dimensional roughened surface, consisting of pyramidal rows, have been presented. Measurements have been taken in a streamwise wall-normal plane intercepting the apex of a row of pyramids and the diagonal of the square base. The results shown in this paper point out the non-homogeneity of the flow in the roughness sub-layer. The different flow behaviour along the ascendant and the descendent part of the pyramids and in the region between two consecutive pyramids has been visualised. Low values of the streamwise component of the mean velocity and high values of the streamwise and wall-normal component of the Reynolds normal stresses, turbulent kinetic energy and Reynolds shear stresses are present in the downstream part of the pyramids, near their base. The mean representation of the flow shows swirling patterns in correspondence of the top of the pyramids. It is suggested that this representation is produced mainly by vortical structures travelling along the wall, retarded and intensified when interacting with the flow around the roughness element and by swirling patterns originating from the interaction of the incoming flow with the pyramids. In order to understand the origin of the high turbulence activity observed downstream the pyramids, near their base, a conditional analysis based on the quadrant method has been performed. It has been shown that sweep events are the major contributor to the very high values of the Reynolds shear stresses observed in this region and are due to the combination of the vortical flow at the top of the pyramid and a large scale (with respect to the roughness element) inflow motion.     

Bubbly turbulent drag reduction is a boundary layer effect

In turbulent Taylor-Couette flow, the injection of bubbles reduces the overall drag. On the other hand, rough walls enhance the overall drag. In this work, we inject bubbles into turbulent Taylor-Couette flow with rough walls (with a Reynolds number up to 4 x 10(5), finding an enhancement of the dimensionless drag as compared to the case without bubbles. The dimensional drag is unchanged. As in the rough-wall case no smooth boundary layers can develop, the results demonstrate that bubbly drag reduction is a pure boundary layer effect.     

Wind-tunnel simulation of thick turbulent boundary layer

An experimental study aimed at revealing the possibility of simulation, in a subsonic wind tunnel, of enhanced Reynolds numbers Re^** via modeling a thick flat-plate boundary layer possessing the properties of a Clauser-equilibrium shear flow is reported. We show that turbulators prepared in the form of variable-height cylinders of height h and diameter d = 3 mm and installed in two rows along the normal to the streamlined wall offer rather an efficient means for modification of turbulent boundary layer in solving the problem. In the majority of cases, mean and fluctuating characteristics of the boundary layer exhibit values typical of naturally developing turbulent boundary layers at a distance of 530 cylinder diameters. The profiles of mean velocity with artificially enhanced boundary-layer thickness can be well approximated, in the law-of-the-wall variables, with the well-known distribution of velocities for canonical boundary layer.     

DNS of compressible turbulent boundary layer over a blunt wedge

Wall turbulence is more complicated than free turbulence, and the direct numerical simulation (DNS) of wall turbulence is more difficult. In recent years, most of DNS cases for wall turbulence are simplified by using temporal mode, where streamwise pe- riodic boundary condition is imposed. In temporal mode, spatial transition will be con- sidered as an analogue of time-evolving transition. For the channel turbulence, an equivalent body force can substitute for the mean gradient of pressure, …     

Experimental study of a supersonic turbulent boundary layer using PIV

Particle image velocimetry was applied to the study of the statistical properties and the coherent structures of a flat plate turbulent boundary layer at Mach 3. The nanoparticles with a good flow-following capability in supersonic flows were adopted as the tracer particles in the present experiments. The results show that the Van Driest transformed mean velocity profile satisfies the incompressible scalings and reveals a log-law region that extends to y/ =0.4, which is further away from the wall than that ...     

Simulation of a thick turbulent boundary layer via a rod grid

A possibility to simulate a thick Clauser-equilibrium incompressible turbulent boundary layer on a flat plate of finite length with the help of a grid formed by cylindrical rods was experimentally examined. A grid with rods oriented parallel to the streamlined surface proved to be an efficient tool enabling modification of the turbulent boundary layer. In most cases, at a distance of 600 rod diameters the time-average and fluctuation characteristics of the modified boundary layer exhibited values typical of a natural turbulent boundary layer. It is shown that the mean velocity profiles with artificially increased boundary-layer thickness can be represented, to a good accuracy, in terms of law-of-the-wall variables, and they can be generalized with a single dependence using an empirical velocity scale in the outside region. The use of a combined method for exerting an influence on the shear flow capable of improving the modeling procedure for turbulent velocity fluctuations in boundary layer is proposed.     

Predetermined control of turbulent boundary layer with a piezoelectric oscillator

With a piezoelectric(PZT) oscillator, the predetermined controls of the turbulent boundary layer(TBL) are effective in reducing the drag force. The stream-wise velocities in the TBL are accurately measured downstream of the oscillator driven by an adjustable power source. The mean velocity profiles in the inner and outer scales are reported and the skin friction stresses with different voltage parameters are compared. Reduction of integral spatial scales in the inner region below y+of 30 suggests that the oscillator at work breaks up the near-wall stream-wise vortices responsible for high skin friction. For the TBL at Reθof 2183, the controls with a frequency of 160 Hz are superior among our experiments and a relative drag reduction rate of 26.83% is exciting. Wavelet analyses provide a reason why the controls with this special frequency perform best.     

DNS of compressible turbulent boundary layer around a sharp cone

Direct numerical simulation of the turbulent boundary layer over a sharp cone with 20° cone angle (or 10° half-cone angle) is performed by using the mixed seventh-order up-wind biased finite difference scheme and sixth-order central difference scheme. The free stream Mach number is 0.7 and free stream unit Reynolds number is 250000/inch. The characteristics of transition and turbulence of the sharp cone boundary layer are compared with those of the flat plate boundary layer. Statistics of fully developed turbulent flow agree well with the experimental and theoretical data for the turbulent flat-plate boundary layer flow. The near wall streak-like structure is shown and the average space between streaks (normalized by the local wall unit) keeps approximately invariable at different streamwise locations. The turbulent energy equation in the cylindrical coordinate is given and turbulent energy budget is studied. The computed results show that the effect of circumferential curvature on turbulence characteristics is not obvious.