简化起落架噪声相似准则及马赫数比例律

doi:10.7527/S1000-6893.2016.0290

Abstract

Abstract:

Noise generated from real aircraft component can be researched through aeroacoustic experiment of scaled model, but some suitable similarity rules must be followed. The frequency similarity rule usually follows Helmholtz number scaling or Strouhal number scaling, and the source strength similarity rule is normally chosen as Mach number similarity in a certain range of Reynolds number. The scaling law of noise magnitude according to the freestream Mach number is useful for applying wind tunnel noise data to real flight condition and estimating the type of noise source. An aeroacoustic experiment of a 1/2 scaled simplified landing gear model of landing gear noise database for civil aviation authority validation (LAGOON) project is carried out in D5 aeroacoustic wind tunnel at Beihang University. Experimental results indicate that the frequency similarity rule of this landing gear model satisfies the Helmholtz number similarity but not the Strouhal number similarity law. The scaling law of landing gear noise according to the freestream Mach number is highly dependent on the frequency. At low frequency range, the noise spectrum satisfies the sixth power scaling law, while at high frequency range the noise spectrum satisfies the seventh power scaling law. A comparison of the transformed noise spectrum of D5 wind tunnel to that of the LAGOON project with the Helmholtz number similarity rule and the corresponding Mach number scaling law shows that the two results agree well with each other.

Key words: landing gear, aeroacoustic wind tunnel, scaled model, similarity rule, scaling law

CLC Number:

V211.7

XING Yu, LIU Peiqing, GUO Hao, XU Liang, LI Ling. Similarity rule and Mach number scaling law for simplified landing gear noise[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(6): 120769-120769.

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Similarity rule and Mach number scaling law for simplified landing gear noise

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