Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-15 DOI:10.1515/tjj-2022-0065

Cheng'an Bai, Chao Zhou

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引用次数: 0

Abstract

Abstract During take-off of a vertical take-off and landing (VTOL) aircraft, ground effects can cause a downward force on the aircraft body and wings. The downward force could substantially reduce the payload of the aircraft, which is undesirable. This paper investigates the ground effects related to VTOL applications with distributed propulsion. A slot jet is used to simulate the distributed propulsion system. A model of a wing with a slot jet placed near the trailing edge of the wing is investigated. The slot jet is almost perpendicular to the ground to provide a vertical thrust. Experimental and numerical methods are used to investigate the aerodynamic performance of this model. Theoretical analysis is carried out to understand the formation mechanism of the low pressure region on the lower surface of the wing, which causes the downward force. The flow physics of the jet inducing ground vortex is investigated. It is found that the convection term in the ground vortex area is the main source of the pressure reduction. Based on the flow mechanism, a redesigned configuration is proposed to reduce the negative effect of the ground vortex. The flow structures such as the tip vortex are also investigated.

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地面效应对垂直起降狭缝式分布式推进系统机翼气动特性的影响

摘要垂直起降(VTOL)飞机在起飞过程中，地面效应会对机体和机翼产生向下的作用力。向下的力可以大大减少飞机的有效载荷，这是不希望的。本文研究了分布式推进垂直起降的地面效应。采用槽型射流对分布式推进系统进行仿真。研究了机翼后缘附近有狭缝射流的机翼模型。狭缝射流几乎垂直于地面，以提供垂直推力。采用实验和数值方法对该模型的气动性能进行了研究。通过理论分析，了解机翼下表面低压区产生下向力的形成机理。研究了射流诱导地涡的流动物理特性。研究发现，地面涡区的对流项是造成压力降低的主要原因。根据流动机理，提出了一种重新设计的结构，以减少地面涡的负面影响。本文还对叶顶涡等流动结构进行了研究。

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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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.