1563 ラバルノズルからの超音速噴流騒音の実験

概要

論文の詳細を見る
The characteristics of supersonic jet noise from a Mach 2.0 nozzle with a thin-nozzle-lip thickness have been experimentally studied over a range of nozzle pressure ratios from 2.0 to 10.0. Acoustic measurements were conducted in an anechoic room providing a free-field environment. Shadowgraph technique was used as the tool to study qualitatively the shock wave patterns which are primarily responsible for shock related noise. The measured screech frequencies under overexpanded conditions are found to agree with Tam's theoretical results.
一般社団法人日本機械学会の論文
2003-08-05