A study was conducted to investigate the computational analysis of Mach number effects on the Edgetone phenomenon. It was demonstrated that the feedback loop of the edgetone was verified by investigating the effect of Mach number. It was observed that the Strouhal number Sr of the peak frequency of the same mode decreased with increasing jet Mach number when the feedback-loop equation in non-dimensional form was correct. It was easy to change the jet Mach number in computational studies, while keeping the Reynolds number fixed. The computational approach was more appropriate to verify the feedback-loop mechanism. The edgetone phenomena of a two-dimensional laminar jet and a triangle wedge were also computed in the study at Mach numbers ranging from 0.087 to 0.435 at three fixed Reynolds numbers, such as 208, 416, and 624.
ASJC Scopus subject areas
- Aerospace Engineering