Investigation of integral surface formulations for acoustic post-processing of unsteady aerodynamic jet simulations

Rahier, Gilles; Prieur, Jean; Vincent, François; Lupoglazoff, Nicolas; Biancherin, Anthoine

doi:10.1016/j.ast.2004.04.005

Cited by 71 publications

(42 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Acoustic surfaces are located very close to the jet, in order to minimize dissipation effects. However, these surfaces are not too close, to avoid fluctuating aerodynamic structures passing through the surface, as discussed by Rahier et al 25 . Here, turbulent structures are presented with the well-known Q-criterion, defined as Q = 1 2 ( ω ij ω ij − s ij s ij ) with s ij and ω ij respectively the symmetric and antisymmetric parts of the velocitygradient tensor.…”

Section: Va Acoustic Fieldmentioning

confidence: 96%

Matched Hybrid Approaches to Predict Jet Noise by Using Large Eddy Simulation

Bodard¹,

Bailly

2009

15th AIAA/CEAS Aeroacoustics Conference (30th AIAA Aeroacoustics Conference)

Self Cite

View full text Add to dashboard Cite

Section: Va Acoustic Fieldmentioning

confidence: 96%

Matched Hybrid Approaches to Predict Jet Noise by Using Large Eddy Simulation

Bodard¹,

Bailly

2009

15th AIAA/CEAS Aeroacoustics Conference (30th AIAA Aeroacoustics Conference)

Self Cite

View full text Add to dashboard Cite

“…As the geometries under consideration are often extremely complex, unstructured codes are a powerful alternative to structured ones, since they offer greater flexibility. The program relies on the Gulfstream Partially Dressed -Closed Cavity Nose Landing Gear (PDCCOnera's classical approach combines (i) an unsteady flow computation with a "Delayed Detached Eddy Simulation" (DDES) method on unstructured grids implemented in the CEDRE 7-9 solver and (ii) a farfield noise computation, from CFD results stored on either solid or porous surfaces, using an integral Ffowcs WilliamsHawkings (FW-H) method implemented in the KIM 10,11 solver. The research program covers the following aspects.…”

Section: Introductionmentioning

confidence: 99%

Further flow and noise predictions of the Gulfstream PDCC nose landing gear on the CEDRE unstructured solver

Sanders¹,

Luquet²,

Lupoglazoff³

et al. 2013

19th AIAA/CEAS Aeroacoustics Conference

Self Cite

View full text Add to dashboard Cite

This paper presents recent achievements at Onera in a global program which objective is to improve the accuracy of numerical predictions of the aerodynamic noise generated by realistic landing gears. The program relies on the Gulfstream Partially Dressed -Closed Cavity Nose Landing Gear (PDCC-NLG), which has been tested at scale 1/3 in the BART aerodynamic windtunnel at NASA LaRC and in the UFAFF acoustic facility at the University of Florida, and is currently proposed in NASA's Benchmark for Airframe Noise Computations (BANC). Onera's numerical approach combines (i) an unsteady flow computation based on a "Delayed Detached Eddy Simulation" (DDES) method (unstructured solver CEDRE) and (ii) a farfield noise computation based on a Ffowcs Williams-Hawkings integral (FW-H) method (KIM solver). The research program covers the following aspects. Firstly, experimental installation effects are compared by using grids representative of the model in the BART (closed test section, case A) and in the UFAFF (open test section, case B). Secondly, two levels of CFD grid resolutions are compared, with grids of about 12M cells (resolution R1) or 70M cells (resolution R2). Thirdly, two different wall models are compared, namely a laminar model (labeled -l) and a turbulent model (labeled -t). In the first steps of the program, already presented in past papers, attention has been focused on, firstly, comparing installation effects with low resolution grids (computationsM1A-l vs. M1B-l) and, secondly, comparing resolutions R1 and R2 on the closed section configuration (computations M1A-l vs. M2A-l). All cited computations were restricted to the laminar wall model. Acoustic predictions have been achieved from data on the rigid surface and on several porous surfaces at various distances from the landing gear. In the present paper, two new DDES computations have been achieved with the highest resolution (R2), one for the "open jet" configuration (B) with the laminar wall model (computation M2B-l) and the other one for the "closed section" configuration (A) with the turbulent wall model (compuation M2A-t). Several parameters are studied, including (i) the influence of the grid resolution on the noise predictions in the open jet configuration, (ii) the sensitivity of the porous surface for FW-H integration to the far-field prediction and (iii) the sensitivity of the wall model to both aerodynamic and acoustic results.

show abstract

“…In the proposed hybrid CAA approach, two Onera in house codes are combined: one, for the flow solution, relies on a DDES (Delayed Detached Eddy Simulation) method implemented in Onera unstructured flow solver CEDRE [6][7][8] and one, for the computation of the far field noise, is based on the Onera code KIM that relies on an integral FW-H (Ffowcs Williams-Hawkings) method [9,10]. [11][12].…”

Section: Introductionmentioning

confidence: 99%

Hybrid CAA solutions for nose landing gear noise

Vincent¹,

Lupoglazoff²,

Luquent³

et al. 2012

18th AIAA/CEAS Aeroacoustics Conference (33rd AIAA Aeroacoustics Conference)

Self Cite

View full text Add to dashboard Cite

Landing gear noise computations require the calculation of unsteady flow fields around complex geometries. Previous experience gained at Onera established the benefit of unstructured grids in CFD computations on both an academic tandem cylinder case and a real life landing gear (LG) complex geometries. The present study extends previous works to assess the noise generated by two different testing configurations of a subscale simplified model of a Gulfstream nose landing gear, namely the Partially Dressed Closed Cavity Nose Landing Gear (PDCC-NLG). This particular test case is proposed in the framework of the Benchmark for Airframe Noise Computations (BANC) managed by NASA LaRC. The proposed hybrid CAA approach associates two Onera in house codes: one, for the flow solution, relies on a DDES (Delayed Detached Eddy Simulation) method implemented in Onera unstructured flow solver CEDRE and one, for the computation of the far field noise, is based on the Onera code KIM that relies on an integral FW-H (Ffowcs WilliamsHawkings) method. Solutions obtained for the PDCC-NLG model in two different facilities are presented and commented. In particular grid sensitivity is discussed by comparing solutions obtained on two different grids for one configuration.

show abstract

Investigation of integral surface formulations for acoustic post-processing of unsteady aerodynamic jet simulations

Cited by 71 publications

References 9 publications

Matched Hybrid Approaches to Predict Jet Noise by Using Large Eddy Simulation

Matched Hybrid Approaches to Predict Jet Noise by Using Large Eddy Simulation

Further flow and noise predictions of the Gulfstream PDCC nose landing gear on the CEDRE unstructured solver

Hybrid CAA solutions for nose landing gear noise

Contact Info

Product

Resources

About