Abstract
The wall pressure fluctuations induced by a subsonic circular jet on a rigid flat plate have been investigated considering two jets with different exit section diameters at the same Mach number. The analysis is aimed at completing the series of papers presented by the authors on the interaction between a subsonic jet and infinite tangential flat plate where the exit Mach number was the only parameter of the jet flow that was varied. In order to analyse other effects out of the Mach number, two configurations with different nozzle exhaust diameters were explored with the objective of isolating the Reynolds number effect keeping fixed the exit Mach number. The nozzle exhaust diameters are 12 mm and 25.4 mm and the instrumented flat plate, installed parallel to the jet flow, is moved at different radial distances from the jet axis. The pressure footprint on the plate has been measured in the stream-wise direction by means of a pair of flush-mounted pressure transducers, providing point-wise pressure signals. Wall pressure fluctuations have been characterised in terms of spectral and statistical quantities. The effect of Reynolds is evidenced and possible scaling relationships that account for the Reynolds dependence are proposed. Implications for modeling the spectral coherence have been considered by the application of the Corcos’ model and the effect of the jet Reynolds number on the model coefficients is analyzed.
Highlights
The wall pressure fluctuations induced by a subsonic circular jet on a rigid flat plate have been investigated considering two jets with different exit section diameters at the same Mach number
At H/D = 2 (Fig. 2a), consistently with the results reported in the literature (e.g.13,19,20), the overall sound pressure level (OASPL) trend is strongly dependent on the stream-wise location
The quadratic dependence of the OASPL on the jet Reynolds number can be explained by the fact that in the first zone, where no interaction occurs between the jet and the surface, the pressure fluctuations intensity is only dependent on the jet mass flow rate, which in turn depends on the nozzle exhaust section
Summary
The wall pressure fluctuations induced by a subsonic circular jet on a rigid flat plate have been investigated considering two jets with different exit section diameters at the same Mach number. By mocking up the aircraft structures with a tangential flat plate, shielding/scattering effects have been investigated (e.g.7,8) and the near- and far-field pressure statistics have been measured[9]. The jet-induced wall pressure field is of interest for predicting the interior noise generation and the vibro-acoustic response of the aircraft surfaces. This aspect has been the subject of a series of investigations performed by the authors on a simplified geometry in incompressible and compressible flow conditions (see[13,14,15])
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