Application of the passive control of shock wave to the reduction of high-speed impulsive noise. (1st January 2011)

• Record Type: Journal Article
• Authors: Doerffer, Piotr; Szulc, Oskar
• Is Part Of: International journal of engineering systems modelling and simulation. Volume 3:Number 1/2(2011)
• Page Start: 64
• Page End: 73
• Publication Date: 2011-01-01
• Subjects: shock wave -- passive control -- perforated wall -- transpiration -- helicopter rotor in hover -- high-speed impulsive noise; Engineering systems -- Computer simulation -- Periodicals; Engineering systems -- Mathematical models -- Periodicals; 620.0042
• DOI: 10.1504/IJESMS.2011.038751
• Languages: English
• ISSNs: 1755-9758

Abstract

Strong, normal shock wave, terminating a local supersonic area on an airfoil (or helicopter blade), not only limits aerodynamic performance but also becomes a source of a high-speed impulsive (HSI) 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 details of the numerical implementation of the Bohning/Doerffer transpiration law into the SPARC code and includes a validation against the experimental data obtained for the ONERA transonic nozzle with a flat wall. The passive control device is then applied numerically on a helicopter blade in high-speed transonic hover conditions to weaken the shock wave – the main source of HSI noise.