This research was made possible through funding from the U.S. Office of Naval Research under Grant No. N000141210337, Deborah Nalchajian and Ronald Joslin.

1. Preparation of Experiments

<ol>
	<li>Select a proper microphone to build the RMP. Use a frequency range of the microphone within the frequency range of interest. 
	NOTE: In this experiment, pressure fluctuations between 100 and 10,000 Hz are of interest. The measurement frequency range of the selected microphone is from 100 to 10,000 Hz. The size of the microphone should be as small as possible, although there are no specific criteria for the size.</li>
	<li>Estimate the sensitivity and frequency response of the RMP system using the analytical method described in the appendix. Adjust the sensitivity and frequency response of the RMP by varying the dimensions of the tubes and structures.</li>
	<li>Use a Dremel to cut the 0.5 mm inner-diameter stainless steel tube into a 5.25 cm long piece.</li>
	<li>With scissors, cut the 1.25-mm inner-diameter soft tube into a 4.75 m long piece.</li>
	<li>Use a milling machine to cut a piece of Plexiglas into a cuboid. The length, width, and height of the cuboid should be 2.54 cm, 1.27 cm, and 1.27 cm, respectively.</li>
	<li>Drill holes with 0.81, 2, 2.56, and 0.76 mm diameters on the Plexiglas cradle, as shown in Figure 2.</li>
	<li>Use a needle drill to make the taper section of the Plexiglas cradle, as shown in Figure 2.</li>
	<li>Look up the microphone sensitivity in the manual provided by the manufacturer, or calibrate the microphone using the method introduced by Wong18.</li>
	<li>Seat the microphone into the Plexiglas cradle, as shown in Figure 2, and fix the microphone using epoxy.</li>
	<li>Connect the stainless-steel tube and the soft tube to the Plexiglas cradle and fix them with epoxy.</li>
	<li>Drill a hole with a 0.81 mm diameter perpendicularly to the model surface at the position of measurement.</li>
</ol>
2. Experiment Setup
<ol>
	<li>Flush mount the primary stainless steel tubes of the RMP sensors to the model surface and add epoxy to fix the stainless steel tubes to the opposite model surface, as shown in Figure 2.</li>
	<li>Surround the RMP with acoustic foam in order to prevent parasitic noise from contaminating the system.</li>
	<li>Route all electrical wiring out of the test section of the tunnel.</li>
	<li>Route the soft anechoic tube out of the test section of the tunnel.</li>
	<li>Connect the end of the soft anechoic tube to a pressure transducer in order to obtain measurements of the mean static pressure simultaneously with the unsteady pressure.</li>
	<li>Connect the RMP to a low-noise amplifier and data acquisition system.</li>
	<li>Set the gain factor of the amplifier to 10. Note that the value of the gain factor can be changed from case to case.</li>
</ol>
3. Calibration
<ol>
	<li>Select a reference microphone that is high quality and has a frequency-independent sensitivity.</li>
	<li>Connect the reference microphone to the input of an amplifier and connect the output of the amplifier to the data acquisition system.</li>
	<li>Set both the input gain and output gain of the amplifier to 10 dB. Note that the gain factor can be varied under different measurement conditions.</li>
	<li>Insert the reference microphone into a pistonphone, as shown in the supplementary figure.</li>
	<li>Turn on the pistonphone.</li>
	<li>Set the acquisition frequency to 4,000 Hz.</li>
	<li>Set the number of samples to 240,000.</li>
	<li>Acquire and save the voltage output from the reference microphone.</li>
	<li>Compute the calibration constant of the reference microphone. The calibration constant, Cref, is the ratio of the standard deviation of the pistonphone-produced sound pressure to the standard deviation of the voltage output of the reference microphone.</li>
	<li>Repeat the calibration process (steps 3.8 and 3.9) several times. Use the mean value, Cref, as the calibration constant.</li>
	<li>Place the reference microphone perpendicularly to the solid surface over which the pressure fluctuation is measured, as shown in Figure 1.</li>
	<li>Align the center of the reference microphone with the RMP tap. Use a distance between the reference microphone and the RMP tap of 1 mm.</li>
	<li>Place the loudspeaker in close proximity to the test model. Use a distance between the loudspeaker and the microphone of 2.5 m for these measurements.</li>
	<li>Connect the loudspeaker to a function generator and turn on the function generator.</li>
	<li>Use the &#34;white noise&#34; option of the function generator to provide the desired acoustic signal and set the root mean square voltage, Vrms, to 0.4 V.</li>
	<li>Adjust the volume of the loudspeaker to the minimum.</li>
	<li>Turn on the loudspeaker.</li>
	<li>Adjust the volume of the loudspeaker amplifier as high as possible without damaging the speaker. Note that most speakers have an indicator light to warn the user if the output amplitude is above the speaker range.</li>
	<li>Acquire and save time-series data from the voltage outputs of both the reference microphone and the RMP using a scanning frequency of 40,000 Hz for 60 sec.</li>
	<li>Compute the time-series values of the sound pressure fluctuation, which is generated by the loudspeaker and function generator and measured by the reference microphone. This is simply the product of the time-series voltage output from the reference microphone, <img alt="Equation 3" src="/files/ftp_upload/53627/53627eq3.jpg" />, and its calibration constant, <img alt="Equation 4" src="/files/ftp_upload/53627/53627eq4.jpg" />; <img alt="Equation 5" src="/files/ftp_upload/53627/53627eq5.jpg" />. Note that the time-series sound pressure, <img alt="Equation 6" src="/files/ftp_upload/53627/53627eq6.jpg" />, is also the pressure fluctuation at the tap of the RMP.</li>
	<li>Compute the time-series sound pressure fluctuation measured by the microphone in the RMP as the product of the time-series voltage output from the RMP, <img alt="Equation 7" src="/files/ftp_upload/53627/53627eq7.jpg" />, and the microphone sensitivity, <img alt="Equation 8" src="/files/ftp_upload/53627/53627eq8.jpg" />; <img alt="Equation 9" src="/files/ftp_upload/53627/53627eq9.jpg" />. Note that the microphone sensitivity, <img alt="Equation 8" src="/files/ftp_upload/53627/53627eq8.jpg" />, should be provided by the manufacturer.</li>
	<li>Compute the auto-spectral density, <img alt="Equation 10" src="/files/ftp_upload/53627/53627eq10.jpg" />, of&#160; <img alt="Equation 11" src="/files/ftp_upload/53627/53627eq11.jpg" />. Compute the auto-spectral density, <img alt="Equation 12" src="/files/ftp_upload/53627/53627eq12.jpg" />, of <img alt="Equation 13" src="/files/ftp_upload/53627/53627eq13.jpg" />. Compute the cross-spectral density, <img alt="Equation 14" src="/files/ftp_upload/53627/53627eq14.jpg" />, between <img alt="Equation 13" src="/files/ftp_upload/53627/53627eq13.jpg" /> and <img alt="Equation 11" src="/files/ftp_upload/53627/53627eq11.jpg" />. The auto-spectral densities and cross-spectral density are defined by Bendat and Piersol19.</li>
	<li>Compute the transfer function as <img alt="Equation 15" src="/files/ftp_upload/53627/53627eq15.jpg" />.</li>
	<li>Compute the coherence function as <img alt="Equation 16" src="/files/ftp_upload/53627/53627eq16.jpg" />, where the asterisk represents the complex conjugate.</li>
	<li>Remove the reference microphone.</li>
	<li>Turn off the loudspeaker and function generator.</li>
	<li>Remove the loudspeaker.</li>
</ol>
4. Data Acquisition
<ol>
	<li>Turn on the wind tunnel.</li>
	<li>Record the time-series voltage output, <img alt="Equation 17" src="/files/ftp_upload/53627/53627eq17.jpg" />, of the RMP with the data acquisition system. Use a scanning frequency of 40,000 Hz. Use a duration of the acquisition of 64 sec.</li>
	<li>Turn off the wind tunnel.</li>
</ol>
5. Data Processing
<ol>
	<li>Compute the sound pressure fluctuation, <img alt="Equation 18" src="/files/ftp_upload/53627/53627eq18.jpg" />, measured by the microphone in the RMP as <img alt="Equation 19" src="/files/ftp_upload/53627/53627eq19.jpg" />.</li>
	<li>Compute the auto-spectral density, <img alt="Equation 20" src="/files/ftp_upload/53627/53627eq20.jpg" />, of the surface pressure fluctuation as <img alt="Equation 21" src="/files/ftp_upload/53627/53627eq21.jpg" />, where <img alt="Equation 22" src="/files/ftp_upload/53627/53627eq22.jpg" /> is the auto-spectral density of the sound pressure fluctuation measured by the microphone in the RMP <img alt="Equation 18" src="/files/ftp_upload/53627/53627eq18.jpg" /> .</li>
</ol>

<ol><li>Blake, W. K. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aBlake%2C+WK+%22Mechanics+of+Flow-induced+sound+and+vibration%22">Mechanics of Flow-induced sound and vibration</a>. , Academic Press. Orlando, FL. (1986).</li>
<li>Schloemer, H. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Effects+of+pressure+gradients+on+turbulent-boundary-layer+wall-pressurefluctuations%5BTitle%5D)+AND+%22J+Acoust+Soc+Am%22%5BJournal%5D)">Effects of pressure gradients on turbulent-boundary-layer wall-pressurefluctuations.</a> J Acoust Soc Am. 42 (1), 93-113 (1967).</li>
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<li>Gautschi, G. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aGautschi%2C+G+%22Piezoelectric+Sensorics%3A+Force%2C+Strain%2C+Pressure%2C+Acceleration+and+Acoustic+Emission+Sensors%2C+Materials+and+Amplifiers%22">Piezoelectric Sensorics: Force, Strain, Pressure, Acceleration and Acoustic Emission Sensors, Materials and Amplifiers</a>. , Springer. Berlin. (2002).</li>
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<li>Huettenbrink, K. B. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aHuettenbrink%2C+KB+%22Lasers+in+Otorhinolaryngology%22">Lasers in Otorhinolaryngology</a>. , Thieme. (2005).</li>
<li>Bell, J. H., Schairer, E. T., Hand, L. A., Mehta, R. D. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Surface+Pressure+Measurement+using+Luminescent+Coatings%5BTitle%5D)+AND+%22Annu+Rev+Fluid+Mech%22%5BJournal%5D)">Surface Pressure Measurement using Luminescent Coatings.</a> Annu Rev Fluid Mech. 33, 155-205 (2001).</li>
<li>Englund, D., Richards, W. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((The+infinite+line+pressure+probe%5BTitle%5D)+AND+%22ISA+Transactions%22%5BJournal%5D)">The infinite line pressure probe.</a> ISA Transactions. 24 (2), 11-19 (1985).</li>
<li>Bergh, H., Tijdeman, H. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Theoretical+and+Experimental+Results+for+the+Dynamic+Response+of+Pressure+Measuring+Systems.+NRL+Report+TR+F+238%5BTitle%5D)+AND+%22National+Aero-and+Astronautical+Research+Inst%22%5BJournal%5D)">Theoretical and Experimental Results for the Dynamic Response of Pressure Measuring Systems. NRL Report TR F 238.</a> National Aero-and Astronautical Research Inst. , Amsterdam. (1965).</li>
<li>Perennes, S., Roger, M. Aerodynamic noise of a two-dimensional wing with high-lift devices. 4th AIAA/CEAS Aeroacoustics Conference, , Toulouse. (1998).</li>
<li>Leclercq, D., Bohineust, X. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Investigation+and+modeling+of+the+wall+pressure+field+beneath+a+turbulent+boundary+layer+at+low+and+medium+frequencies%5BTitle%5D)+AND+%22J+Sound+Vibrat%22%5BJournal%5D)">Investigation and modeling of the wall pressure field beneath a turbulent boundary layer at low and medium frequencies.</a> J Sound Vibrat. 257 (3), 477-501 (2002).</li>
<li>Franzoni, L. P., Elliott, C. M. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((An+innovative+design+of+a+probe-tube+attachment+for+a+half+in+microphone%5BTitle%5D)+AND+%22JASA%22%5BJournal%5D)">An innovative design of a probe-tube attachment for a half in microphone.</a> JASA. 104, 2903-2910 (1998).</li>
<li>Arguillat, B., Ricot, D., Robert, G., Bailly, C. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Measurements+of+the+wavenumber-frequency+spectrum+of+wall+pressure+fluctuations+under+turbulent+flows%5BTitle%5D)+AND+%22Collection+of+Technical+Papers+-+11th+AIAA%2FCEAS+Aeroacoustics+Conference%22%5BJournal%5D)">Measurements of the wavenumber-frequency spectrum of wall pressure fluctuations under turbulent flows.</a> Collection of Technical Papers - 11th AIAA/CEAS Aeroacoustics Conference. 1, 722-739 (2005).</li>
<li>Yang, H., Sims-Williams, D., He, L. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aYang%2C+H+%22Unsteady+pressure+measurement+with+correction+on+tubing+distortion.+Unsteady+Aerodynamics%2C+Aeroacoustics+and+Aeroelasticity+of+Turbomachines%22">Unsteady pressure measurement with correction on tubing distortion. Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines</a>. , Springer. Berlin. 521-529 (2006).</li>
<li>Hoarau, C., Boree, J., Laumonier, J., Gervais, Y. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Analysis+of+the+wall+pressure+trace+downstream+of+a+separated+region+using+extended+proper+orthogonal+decomposition%5BTitle%5D)+AND+%22Phys+Fluids%22%5BJournal%5D)">Analysis of the wall pressure trace downstream of a separated region using extended proper orthogonal decomposition.</a> Phys Fluids. 18 (5), 055107(2006).</li>
<li>Bilka, M. J., Paluta, M. R., Silver, J. C. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Spatial+correlation+of+measured+unsteady+surface+pressure+behind+a+backward-facing+step%5BTitle%5D)+AND+%22EXIF%22%5BJournal%5D)">Spatial correlation of measured unsteady surface pressure behind a backward-facing step.</a> EXIF. 56 (2), (2015).</li>
<li>Probsting, S., Gupta, A., Scarano, F., Guan, Y., Morris, S. C. Tomographic PIV for Beveled Trailing Edge Aeroacoustics. 20th AIAA/CEAS Aeroacoustics Conference, , AIAA Paper (2014).</li>
<li>Wong, G. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aWong%2C+G+%22Microphones+and+Their+Calibration.+Springer+Handbook+of+Acoustics%22">Microphones and Their Calibration. Springer Handbook of Acoustics</a>. , Springer. (2007).</li>
<li>Bendat, J. S., Piersol, A. G. <a target="_blank" href="http://scholar.google.com/scholar?hl=en&safe=off&q=author%3aBendat%2C+JS+%22Random+data%3A+analysis+and+measurement+procedures%22">Random data: analysis and measurement procedures</a>. , John Wiley & Sons. New York, NY. 2nd edition (1986).</li>
<li>Goody, M. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Empirical+spectral+model+of+surface+pressure+fluctuations%5BTitle%5D)+AND+%22Am+Instit+Aero+Astronaut%22%5BJournal%5D)">Empirical spectral model of surface pressure fluctuations.</a> Am Instit Aero Astronaut. 42 (9), 1788-1794 (2004).</li>
<li>Corcos, G. M. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((Resolution+of+pressure+in+turbulence%5BTitle%5D)+AND+%22J+Acoust+Soc+Am%22%5BJournal%5D)">Resolution of pressure in turbulence.</a> J Acoust Soc Am. 35 (2), 192-199 (1963).</li>
<li>Tijdeman, H. <a target="_blank" href="http://www.ncbi.nlm.nih.gov/pubmed?term=((On+the+propagation+of+sound+waves+in+cylindrical+tubes%5BTitle%5D)+AND+%22J+Sound+Vibrat%22%5BJournal%5D)">On the propagation of sound waves in cylindrical tubes.</a> J Sound Vibrat. 39 (1), 1-33 (1975).</li>
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</ol>

The authors have nothing to disclose.

The measurement of USP in wind tunnel experiments is needed for many applications related to aeroacoustics and flow-induced vibrations. Compared to existing methods, such as flush-mounted imbedded sensors, PSP, or vibrated membranes, the method described here allows for accurate measurements with a high sensitivity to large-magnitude fluctuation over a wide range of frequencies. More importantly, it also provides a method for USP measurements using a small sensing area that minimizes the spatial averaging effects describ...

Fluid flow over surfaces generally leads to unsteadiness and turbulence that result in unsteady surface pressure (USP). Flow-induced sound and vibration are often a direct result of this unsteadiness. The radiated sound generated by cooling fans, propellers, and wind turbines are dominated by sources related to USP1. Measurements of the spatial and temporal characteristics of USP in turbulent flows are generally required in order to predict the radiated sound.
The statistical characterization of USP is generally given in the form of auto-spectral density, two-point cross-spectral densities, and spatial correlation functions2, 3. The frequency response required can vary depending on the application. In many wind tunnel applications, a response of 10 kHz to 20 kHz is sufficient. The small scales of turbulent motion often require sensing areas and sensor spacing to be less than 1 mm.
Extensive experimental studies have been conducted in order to obtain turbulence-induced pressure fluctuations. A direct method uses flush-mounted embedded sensors. This method often employs large arrays of microphones, because each sensor can only measure the pressure fluctuation at one discrete point. Typical sensors utilized in this method are piezoelectric transducers, suggested by Gautschi4. Arrays of piezoelectric sensors can be expensive, and the frequency range of measurement is often less than 10 kHz.
Direct surface-mounted microphones are often used as inexpensive USP sensors5. Microphones have high sensitivity, which is a substantial benefit for low-speed flows. However, this also leads to the risk of sensor saturation when large amplitude fluctuations in pressure are present. This method is not suitable for surfaces with large curvatures, discontinuities, or geometries that are too thin to contain the entire sensor.
An indirect method for obtaining both spectral and spatial information is to use thin membranes flush-mounted to a surface6. The time- and space-dependent vibration motions are measured and then converted to surface pressure statistics using known mechanical properties of the membrane. This method requires careful design, implementation, and accurate calibration of the membrane&#39;s dynamic response. Additionally, the vibration measurement equipment, such as laser Doppler vibrometers, are expensive. Lastly, this method can only be applied to flat surfaces.
Pressure-sensitive paint (PSP) is another technique that can be used to measure the unsteady surface pressure. This technique requires the surfaces to be coated in a transparent polymer binder, which causes the molecules within to be excited to a higher energy state as they are illuminated by light of a specific wavelength. As the molecules undergo oxygen quenching, energy is released as light at a rate proportional to the oxygen partial pressure, resulting in luminescence that is inversely proportional to the surface pressure7. The major drawback to PSP methods is the relatively low sensitivity of the measurement when compared to microphones. This limits the application of PSP to relatively high-speed flows.
The present communication describes a method for USP that uses a remote microphone probe (RMP). This method was first described by Englund and Richards8. The concept uses a standard miniature microphone that is connected to the surface pressure tap with a hollow tube. The unsteady pressure at the model surface will travel into the tubing in the form of sound waves. The tubing acts as a &#34;wave-guide&#34; to allow the microphone, which is mounted perpendicularly to the tubing, to measure the sound waves. The waves then continue into another tube that is long enough to eliminate large-amplitude acoustic reflections.
Englund and Richards applied an analytical approach outlined by Bergh and Tijdeman9 to determine the dynamic response of the RMP. Perrenes and Roger10 utilized an RMP to measure surface pressure over a two-dimensional airfoil with high-lift devices. They developed a probe with a 0.5 mm diameter capillary tube at the surface that was connected to a 27-cm-long rigid tube that expanded from 0.7 mm to 2.5 mm via two separate step changes. Each step change caused a relatively large change in the acoustic impedance of the tube. Leclercq and Bohineust11 studied the wall pressure field beneath a turbulent boundary layer. They used a constant-diameter RMP, as suggested by Franzoni and Elliott12. However, the dynamic response was high enough only in a limited frequency range. Arguillat et al.13 designed an RMP to study the noise transmitted to the interior of a vehicle compartment. They tested various tubes to conduct the pressure fluctuation to the microphones. Yang et al.14 corrected for the tubing distortion by using a tubing transfer function approach that is similar to the method introduced in this report. Hoarau et al.15 studied the wall pressure trace downstream of a separated region. The RMPs that they designed had constant inside diameters, and the tubing was entirely non-rigid.
According to previous studies, the accuracy of surface pressure measurements obtained using RMPs is mainly dependent upon the determination of the frequency-dependent transfer function of the probe that relates the surface pressure to the microphone pressure. The following sections will describe an RMP geometry that is both simple and effective. Experimental and analytical methods will be introduced and validated in order to accurately determine the dynamic response of the RMP. The analytical model allows for an RMP to be optimized in the design stage for a potentially wide range of applications.
RMPs can be used to measure pressure fluctuations over a wide range of frequencies. The relatively high spatial resolution can offer detailed information on characteristics of the spatially-distributed unsteady pressure field16. As the probe is small, RMPs can be utilized to measure pressure fluctuations over complex geometries, such as large curvatures or limited spacing17. In addition, the tube connecting the surface tap and the microphone sensor can reduce the magnitude of the induced pressure fluctuation at the microphone. Thus, proper design of RMP sensor geometry and parameters yields a method for obtaining USP characteristics that are significantly less restrictive when compared to flush-mounting the microphone directly to the model surface.
Structure of the RMPThe general structure of the RMP is shown in Figure 1. The RMP consists of one tube leading from the model surface to an expansion section and a second tube extending from the expansion section to a &#34;cradle.&#34; A third tube is then connected to act as an anechoic termination. The cradle is a machined plastic component used for housing the microphone and the tube connections. The details of the RMP structure can be adjusted for various experimental conditions. The purpose of the second, larger-diameter tube is to allow the relatively bulky microphone and cradle to be placed further from the point of the USP measurement without significantly reducing the measurement sensitivity. This second tube can be eliminated if it is not necessary, and the expansion section can be built in the cradle. The anechoic termination was made of soft plastic that was approximately 2 to 3 m in length.
For this demonstration, the design of the RMP was optimized for the measurement of surface pressure fluctuations under a turbulent boundary layer without a streamwise pressure gradient, as shown in Figure 2. The second tube was eliminated. The effects of the two different lengths of the first tube were observed. The first tube was constructed from stainless steel with an inner diameter of 0.5 mm and an outer diameter of 0.81 mm. The lengths of the first tube were 5.35 and 10.40 cm, respectively. The inner diameter of the inlet of the expansion section, which was incorporated into the cradle, was 0.5 mm, and the inner diameter of the exit was 1.25 mm, which was identical to the inner diameter of the dissipation termination. The angle of the expansion section was 7&#176;. There was a hole in the cradle with a 1.25 mm diameter in order to smoothly connect the expansion section with the anechoic termination. The sensing area was connected to the 1.25 mm hole through a perpendicular 0.75 mm hole.

<table><tbody><tr><td>Microphone</td><td>ACO Pacific (http://www.acopacific.com/)</td><td>7016</td><td>Used to measure the sound pressure and calibrate the RMP as a reference.</td></tr><tr><td>Microphone</td><td>Knowles (http://www.knowles.com/eng)</td><td>FG-23629-C36</td><td>Used to measure the pressure fluctuation as a part of the RMP.</td></tr><tr><td>Microbore Tubing</td><td>Saint-gobain (http://www.biopharm.saint-gobain.com/en/index.asp)</td><td>Tygon ND 100-80</td><td>Used to dissipate the sound waves as a dissipation termination.</td></tr><tr><td>Hypodermic Tubing</td><td>MicroGroup (http://www.microgroup.com/)</td><td>304H21RW</td><td>Used to connect the surface tap and allow the surface pressure fluctuation to convect to the microphone in the RMP in the form of sound.</td></tr><tr><td>Hypodermic Tubing</td><td>MicroGroup (http://www.microgroup.com/)</td><td>304H14H</td><td>Used to reduce the dissipative effect and allow the surface pressure fluctuation to convect to the microphone in the RMP in the form of sound.</td></tr><tr><td>plexiglass</td><td>Plaskolite (http://www.plaskolite.com/)</td><td>1X76204A</td><td>Used to make cradles which can connect the tubing and the microphone for the RMP.</td></tr><tr><td>Data acquisition chassis</td><td>National Instruments (http://www.ni.com/)</td><td>PXI-1006</td><td>For data acquisition.</td></tr><tr><td>Data acquisition channel</td><td>National Instruments (http://www.ni.com/)</td><td>PXI-4472</td><td>For data acquisiton.</td></tr><tr><td>Function generator</td><td>thinkSRS (http://www.thinksrs.com/)</td><td>DS360</td><td>To generate white noise signal.</td></tr><tr><td>Pistonphone</td><td>B&amp;amp;K (http://www.bksv.com/)</td><td>4228</td><td>To generate sine waves with constant frequency which will be used to calibrate the reference microphone.</td></tr><tr><td>Loudspeaker</td><td>Mackie (http://www.mackie.com/index.html)</td><td>HD1531</td><td>Used to convert the electrical white noise signal into sound. It is the sound source for calibrating the RMP.</td></tr><tr><td>MatLab</td><td>Mathworks (http://www.mathworks.com/)</td><td></td><td>Used to process experimental data.</td></tr><tr><td>LabVIEW</td><td>National Instruments (http://www.ni.com/)</td><td></td><td>Used control the hardware for data acquisition and record the data.</td></tr></tbody></table>

the measurement of unsteady surface pressure using a remote microphone probe

Microphones are widely applied to measure pressure fluctuations at the walls of solid bodies immersed in turbulent flows. Turbulent motions with various characteristic length scales can result in pressure fluctuations over a wide frequency range. This property of turbulence requires sensing devices to have sufficient sensitivity over a wide range of frequencies. Furthermore, the small characteristic length scales of turbulent structures require small sensing areas and the ability to place the sensors in very close proximity to each other. The complex geometries of the solid bodies, often including large surface curvatures or discontinuities, require the probe to have the ability to be set up in very limited spaces. The development of a remote microphone probe, which is inexpensive, consistent, and repeatable, is described in the present communication. It allows for the measurement of pressure fluctuations with high spatial resolution and dynamic response over a wide range of frequencies. The probe is small enough to be placed within the interior of typical wind tunnel models. The remote microphone probe includes a small, rigid, and hollow tube that penetrates the model surface to form the sensing area. This tube is connected to a standard microphone, at some distance away from the surface, using a "T" junction. An experimental method is introduced to determine the dynamic response of the remote microphone probe. In addition, an analytical method for determining the dynamic response is described. The analytical method can be applied in the design stage to determine the dimensions and properties of the RMP components.

Calibration results from two representative RMP designs are shown in this section. The first one used a 5.35 cm primary tube, and the second one used a 10.4 cm primary tube. The dissipative terminations are 4.75 m long for both RMPs.
The coherence between the pressure fluctuations measured by the microphone in the RMP and by the reference microphone is shown in Figure 3. The data show a near-unity coherence valu...

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The Measurement of Unsteady Surface Pressure Using a Remote Microphone Probe

Here, we present a protocol to measure, with high spatial resolution, the unsteady surface pressure in turbulent flows. This method demonstrates the construction of a remote microphone probe (RMP) and the determination of its frequency-dependent, complex transfer function. An analytical determination of the dynamic response is presented and validated.

Microphones are widely applied to measure pressure fluctuations at the walls of solid bodies immersed in turbulent flows. Turbulent motions with various ...

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6.9K Views.  University of Notre Dame. Here, we present a protocol to measure, with high spatial resolution, the unsteady surface pressure in turbulent flows. This method demonstrates the construction of a remote microphone probe (RMP) and the determination of its frequency-dependent, complex transfer function. An analytical determination of the dynamic response is presented and validated.

Video: The Measurement of Unsteady Surface Pressure Using a Remote Microphone Probe

Exploring the Effects of Atmospheric Forcings on Evaporation: Experimental Integration of the Atmospheric Boundary Layer and Shallow Subsurface

Evaporation is directly influenced by the interactions between the atmosphere, land surface and soil subsurface. This work aims to experimentally study evaporation under various surface boundary conditions to improve our current understanding and characterization of this multiphase phenomenon as well as to validate numerical heat and mass transfer theories that couple Navier-Stokes flow in the atmosphere and Darcian flow in the porous media. Experimental data were collected using a unique soil tank apparatus interfaced with a small climate controlled wind tunnel. The experimental apparatus was instrumented with a suite of state of the art sensor technologies for the continuous and autonomous collection of soil moisture, soil thermal properties, soil and air temperature, relative humidity, and wind speed. This experimental apparatus can be used to generate data under well controlled boundary conditions, allowing for better control and gathering of accurate data at scales of interest not feasible in the field. Induced airflow at several distinct wind speeds over the soil surface resulted in unique behavior of heat and mass transfer during the different evaporative stages.

A protocol for the design and construction of a soil tank interfaced to a small climate controlled wind tunnel to study the effects of atmospheric forcings on evaporation is presented. Both the soil tank and wind tunnel are instrumented with sensor technologies for the continuous in situ measurement of environmental conditions.

Evaporation is directly influenced by the interactions between the atmosphere, land surface and soil subsurface. This work aims to experimentally study ...

Environment

Blast Quantification Using Hopkinson Pressure Bars

Near-field blast load measurement presents an issue to many sensor types as they must endure very aggressive environments and be able to measure pressures up to many hundreds of megapascals. In this respect the simplicity of the Hopkinson pressure bar has a major advantage in that while the measurement end of the Hopkinson bar can endure and be exposed to harsh conditions, the strain gauge mounted to the bar can be affixed some distance away. This allows protective housings to be utilized which protect the strain gauge but do not interfere with the measurement acquisition. The use of an array of pressure bars allows the pressure-time histories at discrete known points to be measured. This article also describes the interpolation routine used to derive pressure-time histories at un-instrumented locations on the plane of interest. Currently the technique has been used to measure loading from high explosives in free air and buried shallowly in various soils.

This protocol details the use of Hopkinson pressure bars to measure reflected blast loading from near-field explosive events. It is capable of interpolating a pressure-time history at any point on a reflective boundary and as such can be used to fully characterize the spatial and temporal variations in loading produced.

Near-field blast load measurement presents an issue to many sensor types as they must endure very aggressive environments and be able to measure pressures ...

Investigating the Three-dimensional Flow Separation Induced by a Model Vocal Fold Polyp

The fluid-structure energy exchange process for normal speech has been studied extensively, but it is not well understood for pathological conditions. Polyps and nodules, which are geometric abnormalities that form on the medial surface of the vocal folds, can disrupt vocal fold dynamics and thus can have devastating consequences on a patient&#39;s ability to communicate. Our laboratory has reported particle image velocimetry (PIV) measurements, within an investigation of a model polyp located on the medial surface of an in&#160;vitro driven vocal fold model, which show that such a geometric abnormality considerably disrupts the glottal jet behavior. This flow field adjustment is a likely reason for the severe degradation of the vocal quality in patients with polyps. A more complete understanding of the formation and propagation of vortical structures from a geometric protuberance, such as a vocal fold polyp, and the resulting influence on the aerodynamic loadings that drive the vocal fold dynamics, is necessary for advancing the treatment of this pathological condition. The present investigation concerns the three-dimensional flow separation induced by a wall-mounted prolate hemispheroid with a 2:1 aspect ratio in cross flow, i.e. a model vocal fold polyp, using an oil-film visualization technique. Unsteady, three-dimensional flow separation and its impact of the wall pressure loading are examined using skin friction line visualization and wall pressure measurements.

Vocal fold polyps can disrupt vocal fold dynamics and thus can have devastating consequences on a patient&#39;s ability to communicate. Three-dimensional flow separation induced by a wall-mounted model polyp and its impact on the wall pressure loading are examined using particle image velocimetry, skin friction line visualization, and wall pressure measurements.

The fluid-structure energy exchange process for normal speech has been studied extensively, but it is not well understood for pathological conditions. ...

Bioengineering

Manufacturing Simple and Inexpensive Soil Surface Temperature and Gravimetric Water Content Sensors

Quantifying temperature and moisture at the soil surface is essential for understanding how soil surface biota respond to changes in the environment. However, at the soil surface these variables are highly dynamic and standard sensors do not explicitly measure temperature or moisture in the upper few millimeters of the soil profile. This paper describes methods for manufacturing simple, inexpensive sensors that simultaneously measure the temperature and moisture of the upper 5 mm of the soil surface. In addition to sensor construction, steps for quality control, as well as for calibration for various substrates, are explained. The sensors incorporate a Type E thermocouple to measure temperature and assess soil moisture by measuring the resistance between two gold-plated metal probes at the end of the sensor at a depth of 5 mm. The methods presented here can be altered to customize probes for different depths or substrates. These sensors have been effective in a variety of environments and have endured months of heavy rains in tropical forests as well as intense solar radiation in deserts of the southwestern U.S. Results demonstrate the effectiveness of these sensors for evaluating warming, drying, and freezing of the soil surface in a global change experiment.

Accurately measuring temperature and water content of the upper 5 mm of the soil surface can improve our understanding of environmental controls on biological, chemical, and physical processes. Here we describe a protocol for manufacturing, calibrating, and conducting measurements with soil surface temperature and moisture sensors.

Quantifying temperature and moisture at the soil surface is essential for understanding how soil surface biota respond to changes in the environment. ...

Measurements of Waves in a Wind-wave Tank Under Steady and Time-varying Wind Forcing

This manuscript describes an experimental procedure that allows obtaining diverse quantitative information on temporal and spatial evolution of water waves excited by time-dependent and steady wind forcing. Capacitance-type wave gauge and Laser Slope Gauge (LSG) are used to measure instantaneous water surface elevation and two components of the instantaneous surface slope at a number of locations along the test section of a wind-wave facility. The computer-controlled blower provides airflow over the water in the tank whose rate can vary in time. In the present experiments, the wind speed in the test section initially increases quickly from rest to the set value. It is then kept constant for the prescribed duration; finally, the airflow is shut down. At the beginning of each experimental run, the water surface is calm and there is no wind. Operation of the blower is initiated simultaneously with the acquisition of data provided by all sensors by a computer; data acquisition continues until the waves in the tank fully decay. Multiple independent runs performed under identical forcing conditions allow determining statistically reliable ensemble-averaged characteristic parameters that quantitatively describe wind-waves&#39; variation in time for the initial development stage as a function of fetch. The procedure also allows characterizing the spatial evolution of the wave field under steady wind forcing, as well as decay of waves in time, once the wind is shut down, as a function of fetch.

This manuscript describes a fully computer-controlled procedure that allows obtaining reliable statistical parameters from experiments of water waves excited by steady and unsteady wind forcing in a small-scale facility.

This manuscript describes an experimental procedure that allows obtaining diverse quantitative information on temporal and spatial evolution of water ...

Measurement of Spatial Stability in Precision Grip

The purpose of the protocol is to indirectly evaluate the direction of the finger force during manipulation of a handheld object based on the biomechanical relationships in which deviated force direction causes center of pressure (COP) replacement. To evaluate this, a thin, flexible, and high spatial resolution pressure sensor sheet is used. The system allows measurement of the COP trajectory in addition to the force amplitude and its temporal regulation. A series of experiments found that increased trajectory length reflected a sensorimotor deficit in stroke patients, and that decreased COP trajectory reflects a compensatory strategy to avoid an object slipping from the hand grip in the elderly. Moreover, the COP trajectory could also be decreased by dual task interference. This article describes the experimental procedure and discusses how finger COP contributes to an understanding of the physiology and pathophysiology of grasping.

The goal of this protocol is to measure the center of pressure (COP) replacement using a high spatial resolution sensor sheet to reflect the spatial stability in a precision grip. The use of this protocol could contribute to greater understanding of the physiology and pathophysiology of grasping.

The purpose of the protocol is to indirectly evaluate the direction of the finger force during manipulation of a handheld object based on the ...

Behavior

A Custom-Made Pressure Transducer System to Record Non-Nutritive Suck Bursts

Non-Nutritive Suck Parameters Measurements Using a Custom Pressure Transducer System

The non-nutritive suck (NNS) device is a transportable, user-friendly pressure transducer system that quantifies infants' NNS behavior on a pacifier. Recording and analysis of the NNS signal using our system can provide measures of an infant's NNS burst duration (s), amplitude (cmH2O), and frequency (Hz). Accurate, reliable, and quantitative assessment of NNS has immense value in serving as a biomarker for future feeding, speech-language, cognitive, and motor development. The NNS device has been used in numerous research lines, some of which have included measuring NNS features to investigate the effects of feeding-related interventions, characterizing NNS development across populations, and correlating sucking behaviors with subsequent neurodevelopment. The device has also been used in environmental health research to examine how exposures in utero can influence infant NNS development. Thus, the overarching goal in research and clinical utilization of the NNS device is to correlate NNS parameters with neurodevelopmental outcomes to identify children at risk for developmental delays and provide rapid early intervention.

Author Spotlight: Implications of Non-Nutritive Sucking on Speech Emergence and Infant Development

The non-nutritive suck (NNS) device can easily collect and quantify NNS features using a pacifier connected to a pressure transducer and recorded through a data acquisition system and laptop. Quantification of NNS parameters can provide valuable insight into a child's current and future neurodevelopment.

The non-nutritive suck (NNS) device is a transportable, user-friendly pressure transducer system that quantifies infants' NNS behavior on a pacifier. ...

Fabrication of a Stable, Biologically Relevant Phantom Material

A Stable Phantom Material for Optical and Acoustic Imaging

Establishing tissue-mimicking biophotonic phantom materials that provide long-term stability are imperative to enable the comparison of biomedical imaging devices across vendors and institutions, support the development of internationally recognized standards, and assist the clinical translation of novel technologies. Here, a manufacturing process is presented that results in a stable, low-cost, tissue-mimicking copolymer-in-oil material for use in photoacoustic, optical, and ultrasound standardization efforts.
The base material consists of mineral oil and a copolymer with defined Chemical Abstract Service (CAS) numbers. The protocol presented here yields a representative material with a speed of sound c(f) = 1,481 &#177; 0.4 m&#183;s-1 at 5 MHz (corresponds to the speed of sound of water at 20 &#176;C), acoustic attenuation &#945;(f) = 6.1 &#177; 0.06 dB&#183;cm-1 at 5 MHz, optical absorption &#181;a(&#955;) = 0.05 &#177; 0.005 mm-1 at 800 nm, and optical scattering &#181;s&#39;(&#955;) = 1 &#177; 0.1 mm-1 at 800 nm. The material allows independent tuning of the acoustic and optical properties by respectively varying the polymer concentration or light scattering (titanium dioxide) and absorbing agents (oil-soluble dye). The fabrication of different phantom designs is displayed and the homogeneity of the resulting test objects is confirmed using photoacoustic imaging.
Due to its facile, repeatable fabrication process and durability, as well as its biologically relevant properties, the material recipe has high promise in multimodal acoustic-optical standardization initiatives.

Author Spotlight: A Stable Phantom Material for Optical and Acoustic Imaging  

This protocol describes the fabrication of a stable, biologically relevant phantom material for optical and acoustic biomedical imaging applications, featuring independently tunable acoustic and optical properties.

Establishing tissue-mimicking biophotonic phantom materials that provide long-term stability are imperative to enable the comparison of biomedical imaging ...

Medicine

Jet Impinging on an Inclined Plate

Source: Ricardo Mejia-Alvarez and Hussam Hikmat Jabbar, Department of Mechanical Engineering, Michigan State University, East Lansing, MI
The goal of this experiment is to demonstrate how a fluid flow exerts forces on structures by conversion of dynamic pressure into static pressure. To this end, we will make a plane jet impinge on a flat plate and will measure the resulting pressure distribution along the plate. The resultant force will be estimated by integrating the product between the pressure distribution and appropriately defined area differentials along the surface of the plate. This experiment will be repeated for two angles of inclination of the plate with respect to the direction of the jet and two flow rates. Each configuration produces a different pressure distribution along the plate, which is the result of different levels of conversion of dynamic pressure into static pressure at the plate's surface.
For this experiment, pressure will be measured with a diaphragm pressure transducer connected to a scanning valve. The plate itself has small perforations called pressure taps that connect to the scanning valve through hoses. The scanning valve sends the pressure from these taps to the pressure transducer one at a time. The pressure induces mechanical deflection on the diaphragm that the pressure transducer converts into voltage. This voltage is proportional to the pressure difference between the two sides of the diaphragm.

Jet Impinging and Conversion of Dynamic Pressure into Static Pressure

Source: Ricardo Mejia-Alvarez and Hussam Hikmat Jabbar, Department of Mechanical Engineering, Michigan State University, East Lansing, MI
The goal of this ...

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Mechanical Engineering

Pressure Transducer: Calibration Using a Pitot-static Tube

Source: Shreyas Narsipur, Mechanical and Aerospace Engineering, North Carolina State University, Raleigh, NC
Fluid pressure is an important flow characteristic that is required to determine the aerodynamics of a system. One of the oldest and still existing pressure measurement systems is the manometer due to its accuracy and simplicity of operation. The manometer is generally a U-shaped glass tube that is partially filled with liquid, as shown in Figure 1. The U-tube manometer requires no calibration because it does not have any moving parts, and its measurements are functions of gravity and the liquid&#39;s density. Therefore, the manometer is a simple and accurate measurement system.
<img src="/files/ftp_upload/10467/10467fig1.jpg" /> 
Figure 1. Schematic of a U-tube manometer.
Real-time pressure measurements are obtained in aircraft by connecting the stagnation and static pressure ports of a pitot-static probe, a device that is commonly used to measure fluid flow pressure, to the ports of a pressure measurement device. This allows pilots to obtain existing flight conditions and to warn them if any changes to the flight conditions occur. While manometers provide very accurate pressure readings, they are inherently bulky. A more realistic solution is needed to measure aircraft pressures, as one of the primary design objectives is to keep the overall aircraft weight as low as possible. Today, electromechanical pressure transducers, which convert the applied pressure to an electric signal, are widely used for pressure sensing applications on aircraft because they are small, lightweight, and can be placed almost anywhere in the airframe. The above characteristics not only help reduce weight but also reduce the amount of tubing required to connect the pitot-static probe to the transducer, thereby decreasing the data response time. Additionally, in experimental aircraft flight testing, miniature pressure transducers come in handy as they allow researchers to maximize pressure data collection without significantly adding to the weight of the aircraft. While different types of pressure transducers with varying measurement techniques exist, one of the more common types of transducer is the capacitive pressure transducer. As transducers are capable of only sending signals in terms of voltage and current, calibration of the transducer is required to relate the strength of a particular signal to the pressure that causes the transducer to generate the signal. The final curve fit that relates the transducer current or voltage to a physical measurement, in our case pressure, is commonly referred to as the transducer calibration curve.
In this experiment, a pitot-static probe is placed in a subsonic wind tunnel with the stagnation and static pressure ports connected to the total and static ports of both the U-tube manometer and the pressure transducer. The wind tunnel is then run at different dynamic pressure settings, and the corresponding pressure reading from the U-tube manometer, and current readings produced by the transducer are recorded. This data is then used to generate calibration curves for the pressure transducer.