• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.10-16
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• 2004

In this paper the aeroacoustic characteristics of a helicopter main rotor system is measured by using a pair of scaled rotor blades. A low noise rotor test jig is developed for noise measurement and the rotational speed, thrust and torque are measured simultaneously in order to match the aerodynamic conditions with the full scale rotor. The accuracy of the force measurement device was checked through a calibration procedure. The measured thurst and torque with a 1.2m rotor are compared to the results of analytical prediction and showed that the thrust data at various rotational speed followed the prediction relatively well, but the torque data considered less accurate. It is also found that the background noise level of the test rig is sufficiently low, and the measured noise level from the rotor can be scaled with rotor tip speed. However, the Mach number dependancy and the directivity changes depend on the noise source characteristics.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.27-36
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• 2006

This paper describes the performance test procedures and results of NRSB-1M and NRSB-2M Not only aerodynamic performance test but also sound measurement test were performed for the small-scaled blades in the ground Total thrusts and torques of the rotor were measured using rotating balance for aerodynamic performance test. Sound pressure levels were measured using microphone in 1.64D distance for sound measurement test. Non-dimensionalized test data are compared and analyzed. Consequently, It was confirmed that NRSB-2 was better than NRSB-1.