The paper investigates different Variable Cycle
TBCC configurations and compares them with
an advanced turbojet for the generic configuration
of a Mach 4.5 supersonic passenger
airliner.
One VCE engine variant and the turbojet are
preliminarily designed and their mass including
air-intake and nozzle is estimated. The airintake
has been sized and pressure recovery and
mass flow in design and off-design conditions is
estimated and subsequently checked by the
Navier-Stokes CFD code Argo
