Supersonic inlet buzz detection using pressure measurement on wind tunnel wall

Farahani, Mohammad; Daliri, Abbas; Sepahi-Younsi, Javad

doi:10.1016/j.ast.2019.02.002

Cited by 20 publications

(6 citation statements)

References 14 publications

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“…With the attachment of a spike, those forebody shapes had achieved a reduced drag of up to 68% (Das et al 2013). Spiked bodies exhibit the strongest form of flow unsteadiness termed 'pulsation' (Kenworthy 1978;Feszty et al 2004a), which under particular flow and geometrical conditions is similar to the 'buzzing' phenomena as observed in a typical supersonic inlet (Farahani et al 2019). The intensity of flow unsteadiness is reported to be remarkedly reduced for the streamlined spiked forebodies (Panaras and Drikakis 2009;Sahoo et al 2016) and for the forebodies with aerodisk-type spikes (Ahmed and Qin 2011;Sahoo et al 2019).…”

Section: Introductionmentioning

confidence: 93%

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Shock-related unsteadiness of axisymmetric spiked bodies in supersonic flow

et al. 2021

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Shock-related unsteadiness over axisymmetric spiked body configurations is experimentally investigated at a freestream supersonic Mach number of 2.0 at 0 • angle of attack. Three different forebody configurations mounted with a sharp spiketip ranging from blunt to streamlined (flat-face, hemispherical, and elliptical) are considered. Steady and unsteady pressure measurements, short-exposure high-speed shadowgraphy, shock footprint analysis from x − t plots, and identification of dominant spatiotemporal modes through modal analysis are carried out to explain the unsteady flow physics. The present investigation tools are validated against the well-known events of 'pulsation' corresponding to the flat-face case. The hemispherical case is characterized by the formation of a separated free shear layer and associated localized shock oscillations. The cycle of charging and ejection of fluid mass from the recirculation zone is identified to drive the flow unsteadiness. Such an event triggers the movement of the separated and reattachment shocks in the opposite direction with respect to each other (out-of-phase shocks motion). In the elliptical case, the overall flow field resembles that of the hemispherical case, except with dampened unsteadiness. The value of the cone angle ( ) associated with the recirculation region is found responsible for the fluctuations caused by the charging and ejection of fluid mass. Thereby, it controls the extent of out-of-phase shocks motion. In the elliptical case, shock unsteadiness is reduced as is observed to be smaller. Based on the gathered results and understanding, the reduction in unsteadiness associated with the aerodisk mounted on the hemispherical forebody is demonstrated and explained via the almost complete elimination of the out-of-phase shocks motion.

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Section: Introductionmentioning

confidence: 93%

“…In general, the strongest form of shock-related unsteadiness is termed as 'buzzing' (Motycka and Murphy 1965;Farahani et al 2019). It is primarily driven by the inviscid unsteady shock phenomena (D'souza et al 1972) and is known to be devastating to the vehicle structure.…”

Section: Introductionmentioning

confidence: 99%

Shock-related unsteadiness of axisymmetric spiked bodies in supersonic flow

et al. 2021

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“…In [ 4 ], experiments were carried out to investigate the pressure fluctuations in the base region of a missile, which can induce an aerodynamic excitation leading to structural failure and stability problems. In [ 5 ], the pressure fluctuations that affect the buzz phenomenon in a supersonic inlet were experimentally investigated. The measurements of the surface pressure fluctuations were also required during the development of the new Space Launcher VEGA-C in order to prevent their effect on structural vibrations that are potentially dangerous for the payload and for other components of the launcher [ 6 ].…”

Section: Introductionmentioning

confidence: 99%

Effect of the Dynamic Response of a Side-Wall Pressure Measurement System on Determining the Pressure Step Signal in a Shock Tube Using a Time-of-Flight Method

Svete

Castro

Kutin

2022

Sensors

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Technological progress demands accurate measurements of rapidly changing pressures. This, in turn, requires the use of dynamically calibrated pressure meters. The shock tube enables the dynamic characterization by applying an almost ideal pressure step change to the pressure sensor under calibration. This paper evaluates the effect of the dynamic response of a side-wall pressure measurement system on the detection of shock wave passage times over the side-wall pressure sensors installed along the shock tube. Furthermore, it evaluates this effect on the reference pressure step signal determined at the end-wall of the driven section using a time-of-flight method. To determine the errors in the detection of the shock front passage times over the centers of the side-wall sensors, a physical model for simulating the dynamic response of the complete measurement chain to the passage of the shock wave was developed. Due to the fact that the use of the physical model requires information about the effective diameter of the pressure sensor, special attention was paid to determining the effective diameter of the side-wall pressure sensors installed along the shock tube. The results show that the relative systematic errors in the pressure step amplitude at the end-wall of the shock tube due to the errors in the detection of the shock front passage times over the side-wall pressure sensors are less than 0.0003%. On the other hand, the systematic errors in the phase lag of the end-wall pressure signal in the calibration frequency range appropriate for high-frequency dynamic pressure applications are up to a few tens of degrees. Since the target phase measurement uncertainty of the pressure sensors used in high-frequency dynamic pressure applications is only a few degrees, the corrections for the systematic errors in the detection of the shock front passage times over the side-wall pressure sensors with the use of the developed physical dynamic model are, therefore, necessary when performing dynamic calibrations of pressure sensors with a shock tube.

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“…Thus, many techniques have been developed so far to obtain the spatiallyresolved information of both physical quantities. Conventionally, people use arrays of thermocouples and pressure taps to collect temperature and pressure data respectively [5]. However, this approach is invasive and can be expensive when a * Author to whom any correspondence should be addressed.…”

Section: Introductionmentioning

confidence: 99%

Single-pixel imaging of temperature/pressure of solid surfaces based on temperature- and pressure-sensitive paint

Jiang¹,

Huang²,

Ju³

et al. 2021

Meas. Sci. Technol.

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Temperature- and pressure-sensitive paints (TSPs/PSPs) are the coatings containing luminescent molecules and sensitive to the temperature and oxygen concentration. This work proposed a single-pixel imaging modality of TSPs/PSPs, which can reconstruct the two-dimensional distribution of the lifetime using the signals acquired by a cost-effective photomultiplier tube. A hybrid algorithm was developed as well to solve the resulting inversion problem. Simulative studies have been conducted to validate and assess the performance of the imaging technique under different parameters including the number of sampling points for each illumination, sampling ratio (SR) and noise level in terms of mean square error, mean relative error (MRE) and computational time. Increasing both the number of sampling points and SR would improve the accuracy but takes more computational time. In the cases of the SR equals to 0.8, the MREs are approximately less than half of the noise level.

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Supersonic inlet buzz detection using pressure measurement on wind tunnel wall

Cited by 20 publications

References 14 publications

Shock-related unsteadiness of axisymmetric spiked bodies in supersonic flow

Shock-related unsteadiness of axisymmetric spiked bodies in supersonic flow

Effect of the Dynamic Response of a Side-Wall Pressure Measurement System on Determining the Pressure Step Signal in a Shock Tube Using a Time-of-Flight Method

Single-pixel imaging of temperature/pressure of solid surfaces based on temperature- and pressure-sensitive paint

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