Research on the Influence of Lip Drooping Angle on the Aerodynamic Performance of Engine Nacelles
Year: 2025
Type: conference-paper
Abstract: The lip drooping Angle, as an important geometric parameter of the nacelle, has a key influence on improving its aerodynamic performance. To achieve the multi-condition collaborative optimization of the aerodynamic performance of the nacelle structure, this study focuses on the nacelle of a certain civil airliner engine. Firstly, the spaceclaim software is used to conduct three-dimensional simulation models and unstructured mesh division for different lip drooping angles. Secondly, the CFD numerical calculation method is adopted to systematically study the Mach number distribution of the nacelle structure at different drooping angles and different flight envelope lines, as well as the variation trends of the drag coefficient C D and the total pressure recovery coefficient σ. The influence of angle changes on the flow separation characteristics at low speeds and the shock wave characteristics at high speeds is summarized. The results show that the 4°droop angle design exhibits significant advantages under all three working conditions. During the take-off stage, the influence of the flow separation zone of this angle model is the smallest. During the climbing and cruising phases, this angle effectively weakens the shock wave intensity. This research has engineering guiding significance for the drag reduction and efficiency improvement design of engines with high bypass ratios.
Authors: Xinzhu Xu, Zhi Wang, ZiJing Wang, Zitong Zhang
Institution: Shenyang Aerospace University
Language: English
Subfield: Computational Mechanics
Field: Engineering
Domain: Physical Sciences
Open Access status: diamond
OpenAlex ID: W4417109580