Computational investigation of slot blowing for fuselage forebody flow control

Aircraft Design Pub Date : 1999-03-01 DOI:10.1016/S1369-8869(99)00006-3

Scott M. Murman , Yehia M. Rizk , Russell M. Cummings , Lewis B. Schiff

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引用次数: 15

Abstract

This paper presents a computational investigation of a tangential slot blowing concept for generating lateral control forces on an aircraft fuselage forebody. This work is aimed at aiding researchers in designing future experimental and computational models of tangential slot blowing. The effects of varying both the jet width and jet exit velocity for a fixed location slot are analyzed. The primary influence on the resulting side force of the forebody is seen to be the jet mass flow rate. This influence is insensitive to different combinations of slot widths and jet velocities over the range of variables considered. Both an actuator plane and an overset grid technique are used to model the tangential slot. The overset method successfully resolves the details of the actual slot geometry, extending the generality of the numerical method. The actuator plane concept predicts side forces similar to those produced by resolving the actual slot geometry.

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机身前体气流控制的狭缝吹气计算研究

本文对飞机机身前体产生侧向操纵力的切缝吹气概念进行了计算研究。这项工作旨在帮助研究人员设计未来切向槽吹的实验和计算模型。分析了射流宽度和射流出口速度对固定位置槽的影响。射流质量流量是影响前体侧向力的主要因素。在考虑的变量范围内，这种影响对狭缝宽度和射流速度的不同组合不敏感。采用致动器平面和覆盖网格技术对切向槽进行建模。该方法成功地解决了实际槽几何的细节，扩展了数值方法的通用性。执行器平面概念预测侧力类似于通过解析实际槽几何形状产生的侧力。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Aircraft Design

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