Aeroacoustic Investigation of High Subsonic Jets in Crossflow

Abstract

The present work investigates the flow and the sound field generated by high subsonic jets in crossflow (JICF). The problem arises when a jet is exhausted perpendicularly into a moving medium. Although being characterized as a very complex flow, the JICF has a well-known fluid dynamics, but a sound field yet to be more explored. Therefore, a hybrid methodology of low computational cost aeroacoustic prediction tool is applied in this work for the complete investigation of this problem. A single jet operating at Mach number 0.75 in a crossflow regime with effective velocity ratios of 4 and 8 is studied herein. The fluid dynamics is solved by the Reynolds Average Navier–Stokes (RANS) equations, and the noise calculations are performed using a statistical method known as the Lighthill Ray-Tracing (LRT) method. The numerical results for the acoustic and flow fields were in reasonable agreement with the experimental data available showing good applicability of this kind of methodology for solving JICF.

The development of an experimental aerodynamics research center in Brazil

“…Different studies in the aeronautical field go through aerodynamic and aeroacoustics analysis of subsonic jets through experimental tests and numerical simulations [9], [10] and [11], comparative studies for the design of propellers [12], characterization of the flow in NACAS and SCOOPS in unconventional aircraft [13] and [14]. These last works developed by CPAERO was in partnership with the aircraft manufacturer FABE Ltda, through the development of a methodology for the design, verification and validation of air intakes for a canard type aircraft (unconventional), as described by [15].…”

“…Applications are seen in field of subsonic jets. For instance, the sound field of subsonic jet in crossflow (JICF) was investigated by [11]. Some of the results were very promising and are illustrated in Fig.…”

“…The symmetry in the plot is clearly seen, as the microphone position is set at Y = 0 or Z = 0. Vc = 8.Source: [11].…”

“…Fig. 37 illustrates some of the results for 1/3 octave-band for sound pressure levels (SPL): Source: [11].…”

“…Fig. 37: Sound pressure level (1/3 octave-band) for configuration A2V6 at (a) 60°; (b) 90° and (c) 120°.Source:[11].…”