Study of two-dimensional and axisymmetric supersonic mixed-compression inlet systems has shown that the geometry of both systems can be varied to provide adequate transonic airflow to satisfy the airflow demand of most jet engines. Collapsing geometry systems for both types of inlet systems provide a generous amount of transonic airflow for any design Mach number inlet system. However, the mechanical practicality of collapsing centerbodies for axisymmetric inlet systems is doubtful. Therefore, translating centerbody axisymmetric inlets with auxiliary airflow systems to augment the transonic airflow capability are an attractive alternative. Estimates show that the capture mass-flow ratio at Mach number 1.0 can be increased approximately 0.20 for a very short axisymmetric inlet system designed for Mach number 2.37. With this increase in mass-flow ratio, even variable-cycle engine transonic airflow demand can be matched without oversizing the inlet at the design Mach number.
Variable geometry for supersonic mixed-compression inlets
American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference ; 1974 ; San Diego, CA
1974-10-01
Conference paper
No indication
English
Flow field in supersonic mixed-compression inlets
NTRS | 1980
|Quasi 1D Modeling of Mixed Compression Supersonic Inlets
British Library Conference Proceedings | 2012
|Quasi 1D Modeling of Mixed Compression Supersonic Inlets
AIAA | 2012
|