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variable geometry for supersonic mixed-compression inletsStudy 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.
Document ID
19750026250
Document Type
Conference Paper
Authors
Sorensen, N. E.
Latham, E. A.
Smeltzer, D. B.
(NASA Ames Research Center Moffett Field, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
October 1, 1974
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
AIAA PAPER 74-1172
Meeting Information
American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference(San Diego, CA)
Distribution Limits
Public
Copyright
Other