攻角
升力系数
空气动力学
二面角
翼
Lift(数据挖掘)
翼型
纵向静稳定性
计算流体力学
机械
俯仰角
地面效应(汽车)
后掠翼
结构工程
航空航天工程
湍流
雷诺数
工程类
计算机科学
物理
量子力学
氢键
数据挖掘
分子
地球物理学
作者
Mojtaba Tahani,Mehran Masdari,Ali Bargestan
出处
期刊:Aircraft Engineering and Aerospace Technology
[Emerald (MCB UP)]
日期:2017-01-03
卷期号:89 (1): 120-132
被引量:7
标识
DOI:10.1108/aeat-05-2015-0139
摘要
Purpose This paper aims to investigate the aerodynamic characteristics as well as static stability of wing-in-ground effect aircraft. The effect of geometrical characteristics, namely, twist angle, dihedral angle, sweep angle and taper ratio are examined. Design/methodology/approach A three-dimensional computational fluid dynamic code is developed to investigate the aerodynamic characteristics of the effect. The turbulent model is utilized for characterization of flow over wing surface. Findings The numerical results show that the maximum change of the drag coefficient depends on the angle of attack, twist angle and ground clearance, in a decreasing order. Also, it is found that the lift coefficient increases as the ground clearance, twist angle and dihedral angle decrease. On the other hand, the sweep angle does not have a significant effect on the lift coefficient for the considered wing section and Reynolds number. Also, as the aerodynamic characteristics increase, the taper ratio befits in trailing state. Practical implications To design an aircraft, the effect of each design parameter needs to be estimated. For this purpose, the sensitivity analysis is used. In this paper, the influence of all parameter against each other including ground clearance, angle of attack, twist angle, dihedral angle and sweep angle for the NACA 6409 are investigated. Originality/value As a summary, the contribution of this paper is to predict the aerodynamic performance for the cruise condition. In this study, the sensitivity of the design parameter on aerodynamic performance can be estimated and the effect of geometrical characteristics has been investigated in detail. Also, the best lift to drag coefficient for the NACA 6409 wing section specifies and two types of taper ratios in ground effect are compared.
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