Passive Control of Shock Wave Applied to Helicopter Rotor High-Speed Impulsive Noise Reduction

• Autorzy: Doerffer P. , Szulc O.
• Języki publikacji: EN

Abstrakty

EN

A strong, normal shock wave, terminating a local supersonic area on an airfoil (or a helicopter blade), not only limits the aerodynamic performance, but also becomes a source of 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 the moving shock. This article describes numerical investigations focused on the application of a passive control device on a helicopter blade in high-speed transonic hover conditions to weaken the shock wave – the main source of HSI noise.

Słowa kluczowe

EN

shock wave; passive control; perforated wall; transpiration

• Wydawca: Politechnika Gdańska
• Czasopismo: TASK Quarterly : scientific bulletin of Academic Computer Centre in Gdansk
• Rocznik: 2010
• Tom: Vol. 14, No 3
• Strony: 297--305
• Opis fizyczny: Bibliogr. 7 poz., rys., tab.

Twórcy

autor

Doerffer P.

autor

Szulc O.

• Institute of Fluid-Flow Machinery, Polish Academy of Sciences, Fiszera 14, 80-952 Gdansk, Poland,

Bibliografia

• [1] Doerffer P and Szulc O 2006 Archives of Mechanics 58 (6) 543
• [2] Caradonna F X and Tung C 1981 Experimental and Analytical Studies of a Model Helicopter Rotor in Hover, NASA Technical Memorandum, 81232
• [3] Doerffer P and Szulc O 2008 TASK Quart. 12 (3) 227
• [4] Magagnato F 1998 TASK Quart. 2 (2) 215
• [5] Doerffer P and Bohning R 2000 Aerospace Science and Technology 4 525
• [6] Doerffer P and Szulc O 2006 6 th Workshop on Modeling of Multiphase Flows in Thermo-Chemical Systems, Stawiska, Poland (on CD)
• [7] Doerffer P and Szulc O 2010 45 th Symposium of Applied Aerodynamics, Marseille, France (on CD)