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Experimental Demonstration of a Supersonic Spike EjectorSpike diffusers are presented as a means to improve supersonic ejector efficiency via reduction in shock losses. Design, fabrication, and testing of an articulated prototype is described. Experimental results are compared to empirical performance curves representing the loci of optimal one- and two-stage conventional ejectors driven by dry air and discharging to atmosphere. Operated at a compression ratio of ~10 with all inputs equal, the spike ejector is shown to have achieved up to 2.19X and 1.83X the secondary mass throughput of the one- and two-stage references, respectively. This suggests the potential of spike diffusers to reduce ejector operating costs by ~50%.
Document ID
20260001044
Acquisition Source
Stennis Space Center
Document Type
Technical Memorandum (TM)
Authors
Daniel R Jones
(Stennis Space Center Bay Saint Louis, United States)
Date Acquired
February 4, 2026
Publication Date
May 1, 2026
Publication Information
Publisher: National Aeronautics and Space Administration
Subject Category
Spacecraft Design, Testing and Performance
Ground Support Systems and Facilities (Space)
Fluid Mechanics and Thermodynamics
Aircraft Propulsion and Power
Aerodynamics
Report/Patent Number
NASA/TM-20260001044
Funding Number(s)
WBS: 750271.09.04.09.96
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert
Keywords
wind tunnel
refrigeration
simulated altitude
vacuum
aerodynamics
experimental
differential expansion
conical shocks
recompression
jet pump
rocket
diffuser
steam
air
supersonic
ejector
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