Numerical simulation of aerodynamic and aeroacoustic characteristics of subsonic rocket sled

Yan, Peize; Zhang, Lishuang; Wang, Yiyun; Jiang, Yi; Pu, Pengyu

doi:10.1016/j.apacoust.2021.108208

Cited by 6 publications

(2 citation statements)

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“…According to Ref. [ 15 ], the vortices between the two connectors of a subsonic rocket sled indicate potential vortex-induced aeroacoustics. This finding aligns with the regions of the high SPL distribution observed in this study.…”

Section: Resultsmentioning

confidence: 99%

“…The combustor pressure and the specific impulse of the sled test were comparable to the results of the laboratory stand firing test using a load cell. The aerodynamic and aeroacoustic characteristics of a dual-rail subsonic rocket sled were simulated by Yan et al [ 15 ]. They found that the vortices between the two connectors were one of the main sources of aerodynamic noise.…”

Section: Introductionmentioning

confidence: 99%

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Sensors Layout Optimization Design of Rocket Sled Test System

Qian,

Wang,

Zhao

et al. 2024

Sensors

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The rocket sled, as a ground dynamic test system, combines the characteristics of the wind tunnel test and the flight test. However, some practical factors, such as shock wave interference, ground effect, and high-intensity aerodynamic noise will cause serious interference and even failure of the uniformly distributed sensors during horizontal sliding in a wide speed range. The AGARD HB-2 standard model is employed as the payload to simulate the aerodynamic and aeroacoustic characteristics during the variable acceleration period, aiming to optimize the test sensors layout. It is observed that in the high Mach number flow fields, strong coupling behaviors among complex waves will occur. The peak of wake vortex strength will appear at 1.5 s and gradually diminish over time. In addition, when the vortex between the load and the booster is monitored, its position shifts forward in the subsonic stage, then gradually moves backward and expands in the supersonic stage. Acoustic directivity is pronounced at subsonic and transonic speeds, pointing towards 75° and 135° relative to the sliding speed, respectively. These results can provide technical support for sensor layout and high-precision testing in rocket sled tests.

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%