전산공력소음해석을 통한 UH-60 제자리비행 공력소음 연구

THE INVESTIGATION FOR UH-60 HOVERING ACOUSTIC NOISE CHARACTERISTIC ANALYSIS BY COMPUTATIONAL AERO-ACOUSTIC METHOD

The helicopter development technology is improved by the increasing of computing power and advanced test facilities. The increasing efficiency of fuel consuming by the developing of improved lift-to-drag rotor system is the major issue, the noise reduction for ecology(civil area) and increase of survivability to reduce noise detection(battlefield) also are important. This investigation shows the helicopter external noise flight test methods, conventional military helicopter's(UH-60) experimental results and the numerical modeling method for aero-acoustic of rotor blade and the result of CAA(Computational Aero-Acoustic) for main rotor blade.