Acoustics of unsteady transonic flow
Abstract
Investigation of noise mechanisms due to unsteady transonic flow is important for aircraft noise reduction. In this work, the near-field impulsive noise due to transonic Blade Vortex Interaction (BVI) and oscillating flap is simulated numerically. These problems are modeled by the two-dimensional high frequency transonic small disturbance equation (VTRAN2 code). The three types of unsteady shock wave motion have been identified. Two different important disturbances exist in the pressure signal. The first disturbance is related to the fluctuating lift and the second is related to the fluctuating drag. Pressure wave signatures, noise frequency spectra, and noise directivity are investigated.
- Publication:
-
Nonsteady Fluid Dynamics
- Pub Date:
- 1990
- Bibcode:
- 1990nfd..symp..187L
- Keywords:
-
- Aeroacoustics;
- Transonic Flow;
- Unsteady Flow;
- Aircraft Noise;
- Blade-Vortex Interaction;
- Noise Reduction;
- Acoustics