热科学学报（英文版）2007，Vol.16Issue(2)：97-104,8.
Shock Wave Strength Reduction by Passive Control Using Perforated Plates
Shock Wave Strength Reduction by Passive Control Using Perforated Plates
Piotr Doerffer 1Oskar Szulc1
作者信息
- 1. Institute of Fluid-Flow Machinery, Polish Academy of Sciences, Fiszera 14, 80-952 Gda(n)sk, Poland
- 折叠
摘要
Abstract
Strong, normal shock wave, terminating a local supersonic area on an airfoil, not only limits aerodynamic performance but also becomes a source of a high-speed impulsive helicopter noise. The application of a passive control system (a cavity covered by a perforated plate) on a rotor blade should reduce the noise created by a moving shock. This article covers the numerical implementation of the Bohning/Doerffer transpiration law into the SPARC code and includes an extended validation against the experimental data for relatively simple geometries of transonic nozzles. It is a first step towards a full simulation of a helicopter rotor equipped with a noise reducing passive control device in hover and in forward flight conditions.关键词
transonic flows/shock wave - boundary layer interaction/passive controlKey words
transonic flows/shock wave - boundary layer interaction/passive control分类
数理科学引用本文复制引用
Piotr Doerffer,Oskar Szulc..Shock Wave Strength Reduction by Passive Control Using Perforated Plates[J].热科学学报（英文版）,2007,16(2):97-104,8.
