Purpose

The main purpose of this study was to determine the basic aerodynamic characteristics of the airliner Tu-154M at the wide range of the overcritical angles of attack and sideslip angles, i.e. α = −900° ÷ 900° and β = −900° ÷ 900°.

Design/methodology/approach

Wind tunnel tests of the Tu-154M aircraft model at the scale 1:20 were performed in a low-speed wind tunnel T-3 by using a six-component internal aerodynamic balance. Several model configurations were also investigated.

Findings

The results of the presented studies showed that at the wide range of the overcritical angles of attack and sideslip angles, i.e. α = −900° ÷ 900° and β = −900° ÷ 900°, the Tu-154M aircraft flap deflection affected the values of the drag and lift coefficients and generally had no major effect on the values of the side force and pitching moment coefficients.

Research limitations/implications

The model vibration which was the result of flow separation at high angles of attack was the wind tunnel test limitation.

Practical implications

Studies of the airliner aerodynamic characteristics at the wide range of the overcritical angles of attack and sideslip angles allow assessment of the aircraft aerodynamic properties during possible unexpected situations when the passenger aircraft is found to have gone beyond the conventional flight envelope.

Social implications

There are no social implications of this study to report.

Originality/value

The presented wind tunnel test results of the airliner aerodynamic characteristics at overcritical angles of attack and sideslip angles is an original contribution to the existing not-too-extensive database available in the literature.

中文翻译：

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客机超临界迎角气动特性实验研究

目的

本研究的主要目的是确定Tu-154M客机在大范围的超临界迎角和侧滑角下的基本气动特性，即α = −900° ÷ 900° 和β = −900° ÷ 900 °。

设计/方法论/途径

Tu-154M飞机模型的1:20比例风洞试验是在T-3低速风洞中使用六部件内部气动平衡进行的。还研究了几种模型配置。

发现

所提出的研究结果表明，在超临界迎角和侧滑角的较宽范围内，即α = −900° ÷ 900° 和β = −900° ÷ 900°，Tu-154M 飞机襟翼偏转影响了阻力和升力系数的值通常对侧向力和俯仰力矩系数的值没有重大影响。

研究局限性/影响

模型振动是高攻角下流动分离的结果，是风洞试验的限制。

实际影响

对超临界迎角和侧滑角范围内的客机空气动力特性的研究可以在客机被发现超出常规飞行包线时评估可能出现的意外情况下的飞机空气动力特性。

社会影响

这项研究没有任何社会影响需要报告。

原创性/价值

所提出的客机在超临界迎角和侧滑角下的空气动力特性的风洞测试结果是对文献中现有的不太广泛的数据库的原创贡献。