This paper presents a numerical and experimental investigation comparing the effectiveness of two sonic boom reduction methods. These methods involve adding and redistributing the lifting volume of an aircraft to shape the shock waves produced by the aircraft and effectively reduce the propagated sonic boom. Applying these methods to existing aircraft, CFD and wind tunnel tests were conducted to compare the shock waves and pressure distribution between unmodified and modified models. From the pressure data, NASA's PCBoom software was used to find the far field pressure distribution of the shock waves as they were propagated towards the ground and measure the intensity of the sonic boom. Based on the results obtained, changing the geometry of aircraft could reduce the intensity of sonic booms.
展开▼
