Research on a sonic boom evaluation and low-boom and low-drag design

Abstract

Kawasaki Heavy Industries, Ltd. has been researching on a sonic boom since 1990 toward the development of the next-generation SST (super sonic transport). A small chamber where a similar-sonic-boom could be created was made in 1993, and over 200 tests were carried out to see the reaction of people inside the chamber. As the result, it was found that A-weighted sound-pressure level (ASEL) and Stevens’ Mark VII perceived level (PL) were good metrics for boom evaluation, and the intolerable levels of ASEL and PL were studied. At the same time, an aerodynamic design technique was developed, which was produced by combining the low-boom theory of Darden (NASA) with the low-drag design method of super sonic aircraft. The validity of the design technique was verified by computational fluid dynamics (CFD) and wind tunnel testing. The effect of trim characteristics on a sonic boom has also been studied for more practical investigations. A boom propagation has also been calculated recently by using Hayes’ program for more understanding. The effects of weight, altitude, and Mach number on a propagating boom were investigated by parametric studies using the next-generation SST configurations in Japan.