The Effect of Jet Exit Pressure on Jets in Supersonic Crossflow

This thesis presents the study of supersonic gas jets used as a fuel injection mechanism in high-speed aircraft engines. Varying the pressure and velocity of the injected jet is found to have a significant effect on not only the mixing and spreading of the jet, but could also potentially alleviate some of the losses incurred during the process. To facilitate part of this study a new supersonic wind tunnel was designed and constructed. The design process and methodologies used are also presented in this thesis.