An experimental program was initiated to determine the noise radiation from landing-gear/wheel-well configurations of large commercial aircraft. Scale models of typical nose gear and main gear (synthesized from different type aircraft) were exposed to flow of typical landing approach speeds (up to 65 m/sec) on a stationary outdoor wall-jet flow facility and attached to the wings of an aerodynamically very clean glider (SB-10). Landing-gear noise is composed of sound generated by the interaction of flow with 1) the wheel-well volume, and 2) the external gear equipment. Wheel-well related sound is characterized by discrete tones whose intensity is heavily damped by the spoiling effect of the gear. Externally generated landing-gear noise is mostly of broadband character. The contributions of some dominant features of a gear (shaft, struts, actuators, doors, wheels) to the total sound signature were determined and normalized nose gear and main gear spectra were developed that predict measured full-scale landing-gear noise fairly well.
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Heller et al. (1977) studied this question.