Noise experiment of an aircraft's landing gear structure

A self-designed submunitiondispenser aerodynamic interference wind tunnel experiment device and the experiment program's feature are introduced. With the device the pressure distribution influence experiment of submunition to its cabin is conducted. The experiment results show that the cabin's pressure distribution represents the transitional type cavity flow while there isn't submuntion, that is to say the region after the front face of the cabin is a low pressure(Cp<0) area which caused by the flow separation, and translate to the region through the point Cp=0. The back face blocks the flow in the cabin, so there is the slowly flow field namely “dead zone” at the corner front back face. The dispenser's angles of attack have an observably effect upon the flow field in the cabin, the positive angle of attack compress the flow, which make the pressure coefficient |Cp| of the flow separation area after the frontface decreased and the longitudinal flow separation region shrank; and that the positive angle of attack of the dispenser also makes the cabin's Cp value of the Cp>0 region increases. The dispenser's negative angle of attack makes the cabin's flow expanded. The effect of submunition to the cabin's flow is compressible but while the submunition is positive angle of attack relative to the dispenser, the compressive effect reduced.