Hybrid LES/RANS Simulations of Transonic Flowfield Around a Rocket Fairing

Tsutsumi, Seiji; Takaki, Ryoji; Takama, Yoshiki; Imagawa, Kichiro; Nakakita, Kazuyuki; Kato, Hideaki

doi:10.2514/6.2012-2900

Cited by 10 publications

(5 citation statements)

References 18 publications

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“…For the unsteady PSP data processing, calibrated unsteady PSP characteristics in eqn. (2) were extrapolated as the unsteady PSP characteristics; Fig. 8 shows the laser illumination area on the test model.…”

Section: Psp Data Processingmentioning

confidence: 99%

“…This wind tunnel campaign 1 Senior Researcher, Wind Tunnel Technology Center, 7-44-1 Jindaiji-Higashi, Chofu, Tokyo, Japan, Senior Member AIAA. 2 Researcher, Space Transportation System Research and Development Center, 7-44-1 Jindaiji-Higashi, Chofu, Tokyo, Japan, Member AIAA. 3 Aerospace Project Researcher, Fluid Dynamics Group, 7-44-1 Jindaiji-Higashi, Chofu, Tokyo, Japan.…”

Section: Introductionmentioning

confidence: 99%

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Unsteady PSP Measurement of Transonic Unsteady Flow Field around a Rocket Fairing Model

Nakakita

Takama

Imagawa

et al. 2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

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Unsteady Pressure-Sensitive Paint (PSP) measurement of a rocket faring model was conducted at the JAXA 2m×2m Transonic Wind Tunnel as a part of the campaign to investigate the steady and unsteady flow field and to obtain the CFD validation data. Unsteady PSP measurement results of M=0.8 and =0 and +4° were described in this paper. Anodized-aluminum PSP (AA-PSP) was coated on the model surface, and it was illuminated by a high-power blue laser diode. AA-PSP luminescence was measured by a high-speed camera, whose frame rate was 5k frame-per-sec. The high-speed camera images were reduced to the time-series Cp distribution images using in-situ method involving pressure transducer data. Several kinds of data analysis were applied to the time-series Cp images and discussed about steady pressure distribution, unsteady pressure variation, and the results of the spectral analysis of the flow field around a rocket faring configuration. Nomenclature A, B, C = Stern-Volmer coefficients= time-series Cp at time t during wind -on condition Kulite P C , = time-average Cp data of Kulite pressure transducer D = Model fuselage diameter, 0.213m I = PSP intensity acquired by high-speed camera I = time-average of wind-on PSP intensity ) (t I = time-series PSP intensity at time t during wind-on condition P = pressure ref = reference condition, 100kPa t = time x = model streamwise location  = Angle of attack of the model

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Section: Psp Data Processingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Unsteady PSP Measurement of Transonic Unsteady Flow Field around a Rocket Fairing Model

Nakakita

Takama

Imagawa

et al. 2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

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“…The spectra evolve very quickly after the centered expansions and very slowly after the gradual expansions. In the area near the expansion corner, there are separation points and reattachment points, a shock wave will appear at each location, and the fluctuating pressure environment will be more complicated [16].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Pressure Fluctuation near an Expansion Corner in a Supersonic Flow of M = 3.01

Zhang

2021

Fluids

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The influence of the expansion corner on pressure fluctuation is an important subject in supersonic flow around high-speed vehicles. Past studies have clarified how the expansion corner alters the root-mean-square of the fluctuating pressure coefficient (Cprms) and the power spectral density (PSD) without considering how these fluctuating properties are related to compressible waves. In this paper, we use characteristics to determine the direction of wave propagation and identified three zones—U-zone, M-zone and D-zone—within which both Cprms and PSD are likely to display different behaviors across the boundary layer. The U-zone is upstream of the characteristic line of the second family and passing through the corner. The D-zone is downstream of the characteristic line of the first family and passing through the corner. The middle zone lies between the U-zone and D-zone. The results of Cprms and PSD at different layers within the boundary layer are obtained using numerical computation through a Detached Eddy Simulation (DES). It is found that in the U-zone and D-zone, both Cprms and PSD are the same in different layers within the boundary layer. In the M-zone, however, both Cprms and PSD may vary in different layers and this variation occurs in the high-frequency band upstream of the corner and mid-frequency band downstream of the corner. A feedback mechanism is tentatively used to explain the difference of spatial distribution of fluctuation properties inside the M-zone.

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“…The launch vehicle is mainly affected by jet noise [1] and aerodynamic noise during flight [2], and the sound pressure level outside the cavity during the launch process can reach more than 170 dB [3]. The external noise of the rocket fairing which poses a threat to the safety of the internal payload is transmitted to the inside of the fairing through transmission and radiation in a wide frequency and random form.…”

Section: Introductionmentioning

confidence: 99%

Experiment-simulation Study on Noise Reduction of Cylinder Shell with Horn Helmholtz Resonator

Yan

et al. 2020

Teh. vjesn.

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This paper focuses on the noise reduction of the cylindrical structure at low frequency (130 Hz-180 Hz). The low-frequency noise response spectrum in the cylindrical cavity is obtained by using the Helmholtz resonator (HR) to reduce the noise peak amplitude. The acoustic simulation software Virtual.Lab is used to establish the finite element model of the cylindrical shell with HR, and to obtain the low-frequency acoustic response in the cylindrical cavity. The simulation model is validated by the experimental results. Then, the influence of installation position, the number of installed resonators and the resonators with different resonance frequencies in the cylindrical cavity are discussed. The results indicate that both the noise reduction band and peak amplitude are increased by installing the HR's on the cylinder shell. The noise reduction of the cylinder shell with HR installed on the upper position is larger than other situations. As the number of resonators increased, the frequency range of the noise reduction in the cylindrical cavity gradually increases, and the noise reduction of the cylinder cavity increases first and then decreases.

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Hybrid LES/RANS Simulations of Transonic Flowfield Around a Rocket Fairing

Cited by 10 publications

References 18 publications

Unsteady PSP Measurement of Transonic Unsteady Flow Field around a Rocket Fairing Model

Unsteady PSP Measurement of Transonic Unsteady Flow Field around a Rocket Fairing Model

Numerical Simulation of Pressure Fluctuation near an Expansion Corner in a Supersonic Flow of M = 3.01

Experiment-simulation Study on Noise Reduction of Cylinder Shell with Horn Helmholtz Resonator

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