Improving inlet performance of turbo-ramjet engine by using surface correction

Abstract

In this study axisymmetric supersonic intake model was tested at Mach number of 4. The intake geometry of SR-71 supersonic aircraft was used here for testing a scale model. Static and total pressure measurements in the duct were used to observe shock effect on internal flow. To improve pressure recovery of intake, surface correction of cone was attempted. By using taper plug different blockage area of exit were obtained to locate normal shock in throat for minimum loss of pressure. Redesign of model, pressure instrumentation, principle of intake operation and data analysis are covered in detail in the thesis. Results of pressure values showed good agreement with simple 1 - D compressible flow calculations.