Using an implicit Finite-Volume Navier-Stokes code the flow field in a Single Expansion Ramp Nozzle (SERN) for a hypersonic aircraft is studied. Comparisons between experimental data and CFD calculations for certain components of the integrated exhaust system (cold 2D nozzle flow, high temperature reacting 3D combustion chamber flow and 2D nozzle flow with external flow) are presented.
To show the sensitivity of the considered components to off-design operating conditions, comprehensive numerical studies have been carried out.
For the determination of nozzle performance a detailed 20 analysis from transonic to hypersonic flight Mach numbers has been performed. A direct optimization method has been used to investigate the influence of the lower nozzle flap shape on the thrust vector.