Investigation of Reynolds Number Effects on Aerodynamic Characteristics of a Transport Aircraft
| Autor: | Xin Xu, Guoshuai Li, Yuan-jing Wang, Da-wei Liu |
|---|---|
| Rok vydání: | 2021 |
| Předmět: |
Aerospace Engineering
02 engineering and technology Computational fluid dynamics Reynolds number effects 01 natural sciences 010305 fluids & plasmas Physics::Fluid Dynamics symbols.namesake Flow separation 0203 mechanical engineering 0103 physical sciences Motor vehicles. Aeronautics. Astronautics Wind tunnel Physics aerodynamic characteristics business.industry Reynolds number transport aircraft TL1-4050 Aerodynamics Mechanics Aerodynamic force Boundary layer 020303 mechanical engineering & transports Mach number symbols business |
| Zdroj: | Aerospace, Vol 8, Iss 177, p 177 (2021) Aerospace Volume 8 Issue 7 |
| ISSN: | 2226-4310 |
| DOI: | 10.3390/aerospace8070177 |
| Popis: | The scale difference between the real flight vehicle and the experimental model results in the Reynolds number effect, which makes it unreliable to predict the aerodynamic characteristics of flight vehicles by wind tunnel testing. To understand the mechanism of Reynolds number effects on the aerodynamic characteristics of the supercritical wing that is commonly used in transport aircraft in more detail, surface pressure wind tunnel tests of a transport aircraft reference model with a wing-body configuration were conducted in the European Transonic Windtunnel (ETW) at different Reynolds numbers. There are 495 pressure taps in total equipped on the surface of the test model with the Mach numbers ranging from 0.6 to 0.86 and Reynolds number varying from 3.3 × 106 to 35 × 106. In addition, an in-house developed CFD tool that has been validated by extensive experimental data was used to correct the wing deformation effect of the test model and achieve detailed flow structures. The results show that the Reynolds number has a significant impact on the boundary layer displacement thickness, surface pressure distribution, shock wave position, and overall aerodynamic force coefficients of the transport aircraft in the presence of shock wave and the induced boundary layer separation. The wind tunnel data combined with flow fields achieved from CFD show that the essence of the Reynolds number effect on the aerodynamic characteristics of transport aircraft is the difference of boundary layer development, shock wave/boundary layer interaction, and induced flow separation at different Reynolds numbers. |
| Databáze: | OpenAIRE |
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