Numerical Studies On Effect Of Changing Mach Number On Aero Disk Model On Flow Contours And Drag Force

• Published in: IOP conference series. Materials Science and Engineering 2018-06, Vol.377 (1), p.12096
• Main Authors: Sai Krishna Mohan, K V N B, Bandaru, Kushaal, Prabhudev, B M
• Format: Article
• Language: English
• Subjects: Computing time; Contours; Drag; Hypersonic flow; Mach number; Pressure; Separation; Shock waves; Supersonic aircraft
• ISSN: 1757-8981; 1757-899X
• DOI: 10.1088/1757-899X/377/1/012096

A supersonic aircraft needs to travel in the atmosphere at different Mach numbers. In this paper the effect of Mach number on a body in hypersonic flow is studied. Also the effect of scaling on the flow behaviour is studied. As the original geometry taking more computational time, scaled model is used for further research. The geometry is modelled, meshed and solved in Ansys tool. Results are compared with available literature and further parametric study is done. There was no appreciable change found in the results obtained by scaled model compared with actual model. Hence Actual body[1] was scaled to 1/10th of its original scale body and simulated at different Mach numbers. The spike of the cone is fitted with an aero disk. Results shows that the angle of the bow shock inclined to body is found to be decreasing as the Mach number is increasing. Two separate shockwaves from disc and cone were found merged at higher Mach numbers. At starting Mach numbers the separation region was unaltered but after Mach number 3, Mach number contours show that flow deflected from aero disk has greater role in deciding the separation region ahead of cone. Further surface pressure graphs are plotted and effect on drag force were discussed.