二次元静止翼から発生する離散周波数騒音の研究 : 翼面上の境界層不安定

概要

論文の詳細を見る
Discrete tone noise generated in a uniform jet flow on a two-dimensional wing was investigated. Discrete tone noise is generated by a self-excited feedback loop formed by the acoustic field and the unstable boundary layer. In this work, we show the calculation method and results of flow fluctuation amplitudes, phase delays and the growth factor, for the unstable boundary layer. The theory of stability of laminar flows and the differential approximation apply to this method. The results are compared with experimental data and almost coincide with them. It is clarified that the flow fluctuation amplitude ratio on the suction side of the wing is larger than on the pressure side The growth factor and the length of the flow fluctuation waves are estimated for all frequencies
一般社団法人日本機械学会の論文
1996-07-25