基于射流飞控技术的环量控制阶段数值研究

王睿雯; 毕殿方; 黄旭东

doi:10.16511/j.cnki.qhdxxb.2023.26.032

清华大学学报（自然科学版） >

2024 , Vol. 64 >Issue 2: 346 - 357

DOI: https://doi.org/10.16511/j.cnki.qhdxxb.2023.26.032

航天航空工程

基于射流飞控技术的环量控制阶段数值研究

王睿雯 ,
毕殿方 ,
黄旭东

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清华大学航天航空学院, 北京 100084

王睿雯(1999-),女,硕士研究生。

收稿日期: 2023-01-04

网络出版日期: 2023-12-28

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Numerical study of circulation control phase based on fluidic flight control technology

WANG Ruiwen ,
BI Dianfang ,
HUANG Xudong

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School of Aerospace Engineering, Tsinghua University, Beijing 100084, China

Received date: 2023-01-04

Online published: 2023-12-28

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摘要

环量控制技术通过调节射流喷气量实现翼型气动性能的提升，在Coanda效应作用下，翼型环量会发生改变，且尾缘后流场出现分离。目前环量控制的分离位置与射流位置、射流高度及射流强度的关系尚不明确。该文主要研究了Coanda效应对流场分布及升阻力特性的影响，并对环量控制的不同控制阶段进行了分析。首先，对NACA0012标准翼型进行尾缘修型，改变尾缘曲率和喷口高度等参数，验证环量控制的有效性；其次，在考虑攻角、动量系数、射流速度3个关键参数的情况下，引入Coanda偏转角，揭示了环量控制的Coanda效应的触发及抑制机理；最后，对NACA0012修型翼型和CC-E0020EJ环量控制翼型提出了分离预测思路。针对环量控制技术中2个控制阶段，通过推阻分解法对升力、阻力进行解构，解释了尾缘后流场分离与再附的超临界现象，提出了分离区域的分析方法。结果表明： Coanda偏转角可以作为动量系数与升力系数的物理判据，翼型下表面的压力损失导致超环量阶段的射流效率降低。

关键词： 环量控制; Coanda效应; 失速特性; 射流飞行控制; 气动增升

本文引用格式

王睿雯 , 毕殿方 , 黄旭东 . 基于射流飞控技术的环量控制阶段数值研究[J]. 清华大学学报（自然科学版）, 2024 , 64(2) : 346 -357 . DOI: 10.16511/j.cnki.qhdxxb.2023.26.032

Abstract

[Objective] Circulation control is a typical fluidic flight control technology that is often used to improve the aerodynamics of aircraft and wind turbine blades. The aerodynamic performance of an airfoil can be improved by adjusting the mass flow rate of the jet. The impact of the Coanda effect on the trailing-edge jet produces a wall-attachment effect, decreasing the trend of flow separation. The researchers adjusted the airfoil circulation by controlling the trailing-edge jet separation. However, the relationship between the trailing-edge jet separation position in circulation control technology and the jet position, jet height, and jet intensity is unclear numerically. [Methods] To solve the problem of trailing-edge jet deflection, this paper mainly investigated the influence of the Coanda effect on the flow field distribution and lift-drag characteristics and analyzed the aerodynamic characteristics at different control stages of circulation control to contribute to the promotion of jet flight control technology. Because of the advancements in computer technology, computational fluid dynamics had considerably improved, and the simulation results for the complex structure of the flow field had reflected the real physical laws. In this paper, the NACA0012 airfoil was modified, and two dimensionless parameters, trailing-edge curvature and jet height, were changed to verify the effectiveness of the Coanda effect under circulation control. Furthermore, several key parameters, such as angle of attack, momentum coefficient, and jet velocity, were simulated using the CFD++ aerodynamic simulation software. Referring to other researchers' work, the concept of the Coanda deflection angle was introduced to reveal the triggering and suppressing mechanisms of the Coanda effect numerically. Thus, the separation prediction method was proposed for the modified NACA0012 airfoil and CC-E0020EJ circulation control airfoil (two symmetrical airfoils). For the two control stages in circulation control technology, this paper deconstructed the lift and drag forces through the push-drag decomposition method, explained the supercritical phenomenon of flow field separation and reattachment behind the trailing edge, and proposed a separation region analysis method. [Results] (1) The most important factor affecting the lift-drag ratio of airfoil trailing-edge parameters was jet nozzle height. When the chord position (x_jet/c) was 0.900, and the nozzle height (h/r) was 7.16%, the lift coefficient generated by the Coanda effect considerably increased, and the best effective lift-drag ratio increased to 43. (2) At a zero angle of attack, the variation trend of the Coanda deflection angle with momentum coefficient was highly consistent with the logarithmic relation curve and the same change characteristics of turning point and growth rate were detected on the symmetrical airfoil, indicating that the Coanda deflection angle was a physical criterion for judging the jet strength and increment of the lift coefficient. (3) The concept of "step zone" was introduced at a nonzero angle of attack, and the strong linear relationship between the jet influence zone position and momentum coefficient at 4? 8? 12? and 16?angles of attack was demonstrated. The large area separation in the trailing edge caused a surge in drag coefficient and loss of lift growth. [Conclusions] The analysis method proposed in this paper achieves the expected goal and provides an effective basis for judging the Coanda effect in fluidic flight control.

Key words： circulation control; Coanda effect; stall characteristic; fluidic flight control; pneumatic rising

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