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Details on the Computation of Hypersonic Inlet Flows
Author(s) -
Reinartz B.,
Ballmann J.
Publication year - 2003
Publication title -
pamm
Language(s) - English
Resource type - Journals
ISSN - 1617-7061
DOI - 10.1002/pamm.200310147
Subject(s) - inlet , aerospace , isolator , compression (physics) , hypersonic speed , aerospace engineering , computation , flow (mathematics) , overall pressure ratio , mechanics , mechanical engineering , structural engineering , materials science , engineering , computer science , physics , algorithm , composite material , electronic engineering , gas compressor
Within the frame of the Collaborative Research Center (SFB) “Fundamentals of Design of Aerospace Planes”, the design criteria of hypersonic engine inlet flows are studied computationally as well as experimentally. Of special interest are geometrical considerations with respect to the attainable total pressure recovery as well as the thermal load on the engine structure. Thus, the length and base angle of the exterior compression ramps are varied and their influence on the overall pressure gain is investigated. In addition, the length of the subsequent isolator/diffusor, responsible for the interior flow compression, is analyzed with emphasis on the total pressure loss.