^{1}

^{*}

^{2}

^{*}

Time sequence signals of instantaneous longitudinal and normal velocity components at different longitudinal and normal positions in a turbulent boundary layer have been finely measured simultaneously by IFA300 constant temperature anemometer and double-sensor hot-wire probe with sampling resolution higher than the frequency that corresponds to the smallest time scale of Kolmogorov dissipation scale before/after introducing artificial periodic blow/suction perturbation. The period-phase-average technique is applied to extract the periodic waveforms of artificial perturbation from instantaneous time sequence signals of longitudinal and normal turbulence background. Experimental investigation is carried out on the attenuation characteristics of periodic perturbation wave with different frequency along longitudinal direction and normal direction in a turbulent boundary layer. The amplitude distributions of longitudinal and normal disturbing velocity component for different perturbation frequencies are measured at different downstream and normal positions in turbulent boundary layer. The amplitude growth rate of artificial periodic perturbation wave is calculated according to flow instability theory. The experimental results are compared and in consistent with the theoretical and numerical results.

Since Kline (1967) [

Inspired by the success of imposing artificial periodic perturbation in lamina boundary layer transition experiment, adopting different methods to introduce artificial periodic perturbation to turbulent boundary layer and examining the influence of artificial periodic perturbations on the burst can solve, from another point of view, the problem of whether the burst time scale is influenced by outer or inner flow conditions. Hussain et al. [11,12] introduced perturbation in the fully developed two-dimensional turbulent channel flow by using electromagnetic excitation method and got a result which is in agreement well with Landahl’s [

Theoretical researches are mainly focused on the development of sinusoidal wave perturbation by the method of lamina instability. Researches in this field started from M. Landahl’s waveguide model. The numerical results are in agreement with Willmarth’s [

In this experiment, periodic artificial blow/suction perturbations of different frequencies are introduced into a turbulent boundary layer through a spanwise slot by exciting a woofer vibrating under the wall in order to manipulate the multi-scale flow structure in turbulent boundary layer. The evolution and the influence of periodic blow/suction perturbation on the turbulent boundary layer are investigated experimentally. Periodic blowing and suction disturbance provides a simple method for wall-bounded turbulence control because the frequency and amplitude of blowing & suction disturbance is able to be quantified and adjusted easily and accurately.

Time sequence signals of longitudinal and normal velocity components at different longitudinal and normal positions in a turbulent boundary layer have been finely measured before/after introducing periodic blow/suction perturbation by IFA300 constant temperature anemometer and TSI-1243 double-sensor hot-wire probe with sampling resolution higher than the frequency that corresponds to the smallest time scale of turbulence. In this paper, experimental results under the conditions of different perturbation were compared and analyzed statistically. Sampling frequency of the experiment is 20 KHz; measuring time for each sampling space point is 13.1072 seconds, and data volume is 262,144.

The experiment is carried out in the low-turbulent level wind tunnel of the Fluid Mechanics Laboratory of Tianjian University. The test section of wind tunnel is made of wood; the cross-section of the test section is a rectangular without corner, with 4500 mm in length, 450 mm in height, and 350 mm in width. Wind velocity in the test section can be continuously adjusted from 1.0 m/s to 40.0 m/s, and the background turbulent level is less than 0.07%. Experimental apparatus arrangement is shown in

the leading edge of the flat plate, The origin of the coordinate axes is located at the center point of the downstream edge of the spanwise slot. The longitudinal direction is x and the normal direction is y. A signal generator is used to produce sinusoidal wave signals with controllable frequency. The sinusoidal wave signals are amplified by a power amplifier to power a 300 mm-diametered woofer periodically, introducing blow/suction perturbation airflow into the turbulent boundary layer, the amplitude of the perturbation is controlled by the amplifier’s power output.

TSI Company’s IFA300 constant temperature anemometer is used, together with CCTS-1193E automatic controlled three-dimensional coordinate frame and Thermalpro software package to carry out the instantaneous velocity measurement automatically. The sensor is a TSI- 1243-T1.5 × type hot-wire probe with double slantwise hot-wires made of 5 μm diameter tungsten fine filament, and the probe is calibrated on the TSI-1128 hot-wire probe calibrator before used.

The mean velocity profiles with/without different frequency perturbations at two locations X = 5 mm X = 5 mm X = 10 mm X = 20 mm X = 30 mm downstream respectively the disturbing source are plotted by inner variable unit in

The eigenwaveform of the periodic artificial perturbation wave is educed by the phase-align period average technique. It is convenient to represent the velocity field as a superposition of three parts:

Here j = 1, 2, 3 stands for velocity components of three directions, is the mean velocity over a long time period, is phase average of periodic perturbation,

and corresponds to the background random fluctuation. The mean velocity can be determined by average over a long time (long time average of and

are = 0, = 0), can be obtained through the phase-align period average method, and the phase average of the instantaneous velocity then gives the sum of the mean and the organized wave. Denoting the phase average by, we have

and then,

The instantaneous velocity is measured at seven longitudinal positions downstream from the perturbation source; the amplitude and eigenwaveform of the perturbation are measured by the phase-average technique.

It is usual to represent the two-dimensional perturbation wave as:

where * stands for complex conjugate, is the twodimensional complex eigenmode, is the complex wavenumber, being the longitudinal wave number and the growth rate factor, and is the complex wave speed.

The perturbation velocity amplitudes at two different longitudinal stations, with the same distance y from the wall

The amplitudes ratio:

that is

there by,

If the perturbation amplitude increases along the longitudinal direction, thus

that is

and then is obtained according to.

If perturbation attenuations along the longitudinal direction, thus

that is

and then is obtained according to.

It is known from above that for the same y value, wave amplitudes at different longitudinal stations of x, perturbation wave amplitude growth rate can be calculated from Equation (7).

^{+} > 100) caused by the 16 Hz and 32 Hz perturbation is much larger than that in the near wall region (y^{+} < 100). It implies that the periodic perturbation in the near wall region causes the response on the outer region, and it shows further the inner and outer boundary layer are not absolutely separated and they are sensible closely each other. The emergence of inner layer’s burst is intimately related to the outer boundary layer’s flow conditions.

While the 64 Hz perturbation distorts seriously in the turbulent boundary layer, the attenuations are relatively rapid, and fails to produce relatively large amplitude perturbation wave’s response in the outer region (y^{+} > 100), which is related to the inherent predominant eigenmode of the turbulent boundary layer, as shown in ^{+} = 12, before and after different frequencies perturbations different frequencies are introduced, the velocity fluctuation power spectrum across the scale parameters (frequency components). It is found that there exists a most energetic scale a = 6 (corresponding to 128 Hz) when no perturbation is introduced. After 16 Hz perturbation has been introduced, the turbulent energy decreases on the Scales 1 ~ 7 and increases on Scales 8 ~ 11, the peak change to Scale 9 (corresponding to 16 Hz). Similarly, for the perturbation frequency of 32 Hz and 64 Hz, the largest containing energy scale changes respectively to a = 8 (32 Hz) and

a = 7 (64 Hz). This shows that different frequencies periodic perturbations change the inherent frequency components of the velocity fluctuation in turbulent boundary layer. 64 Hz perturbation is the nearest frequency to the inherent main frequency of the velocity fluctuation in turbulent boundary layer, and the interaction with the

inherent frequency components in the turbulent boundary layer is the strongest. Thereby, the 64 Hz perturbation in turbulent boundary layer distorts seriously and attenuations rapidly, and cannot lead to large response in the outer region y^{+} > 100. Suppose, the frequency of the perturbation wave is 128 Hz (Scale 6), thus, it just fits the inherent frequency of the velocity fluctuation power spectrum in turbulent boundary layer, and its interaction with the frequency components in turbulent boundary layer is the strongest. It could attenuation most rapidly in turbulent boundary layer and cannot induce large response y^{+} > 100.

Yao [

Therefore, he concluded that the perturbation, which is most close to the inherent main frequency of the turbulent fluctuation energy in a turbulent boundary layer and has the interaction with the frequency components in the turbulent boundary layer strongest, attenuations most rapidly, and the response in the outer region of turbulent boundary layer is the weakest. As the perturbations travel to the downstream, perturbation becomes weaken gradually and its influence disappears when x = 40 mm, the velocity fluctuation power spectrum recover to the case when no perturbation happens.

Linear and nonlinear stability theoretical calculation indicates that there is no overall instability in turbulent boundary layer, for the turbulence is a dynamic equilibrium and stable state. Perturbation waves at different frequencies under normal circumstances trend to attenuation. Figures 6-8 are respectively the amplitude growth rate distribution of the perturbation wave of 16 Hz, 32 Hz and 64 Hz. The perturbation wave amplitudes trend to attenuation on the whole, that is, the overall amplitude growth rate of the perturbation wave is, with sometimes local amplitude growth rate is, and the development of the perturbation wave amplitude is not

always monotonous. The attenuation rate of 16 Hz and 32 Hz perturbation in the near wall region close to the perturbation source (y^{+} < 100) is weak, while in the outer region is comparatively strong, but the attenuation rate along the longitudinal direction weakens gradually. The 64 Hz perturbation attenuations quickly in the whole flow field, because the 64 Hz perturbation is the most approaching to the inherent burst frequency of the turbulence and the interaction between the perturbation wave and turbulence is the strongest, perturbation wave attenuations most rapidly in turbulent boundary layer.

1) The inner and outer layers are not absolutely separated. They have the relationship of receptivity. The emergence of inner layer’s burst is intimatly related to the outer boundary layer’s flow conditions.

2) Perturbation waves at different frequencies under normal circumstances trend to attenuation. The amplitude of perturbation waves of different frequencies generally attenuations along the longitudinal direction and trends to become weaker gradually. But the perturbation wave amplitude does not always monotonously decrease with sometimes local amplitude growth rate is negative.

3) The 16 Hz and 32 Hz perturbation wave attenuations in a distance close to the perturbation source along the longitudinal direction, while their response is relatively strong in the area outside the logarithm law district. The perturbation at frequency that is the most approaching to the inherent burst frequency in turbulent boundary layer attenuations relatively rapid in the whole boundary layer.

4) The perturbation amplitude attenuation rate measured in this experiment is in agreement with the results analyzed and calculated by M. Landahl’s (1967) theory analysis.