High-altitude air inlet pressure distortion test method for small-bypass-ratio aero-engine

The invention provides a small-bypass-ratio aero-engine high-altitude air inlet pressure distortion test method which comprises the steps: a numerical simulation technology is applied, the pneumatic flow field condition in a flow pipe during an engine maximum state test is simulated, the position of...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	TIAN YINGWEI, WU FENG, LIU ZHIYOU, PENG SHENGHONG
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	MEASURING PHYSICS TESTING TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR
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