(ISTFD 2023)

27-29 July 2023, Nanjing, China


Zhansen Qian

AVIC Aerodynamics Research Institute, 

Key Laboratory of Hypersonic Aerodynamic Force and Heat Technology, China

Dr. Zhansen Qian obtained his Ph.D. in Aerodynamics in School of Aeronautic Science and Engineering in Beihang University, China in 2011. He served as the executive editor of Journal Aerodynamic Research and Experiment (ARE, a Chinese journal), the deputy editor of Journal Physics of Gases (PoG, a Chinese journal), and the editorial board of several journals such as Acta Aerodynamica Sinica (AAS, a Chinese journal) & Advances in Aerodynamics (AIA). He also served as Executive member of China Aerodynamics Society (CAS), Vice Director of Computational Aerodynamics Committee of China Aerodynamics Society (CAS); Member of International Cooperation Working Committee, and Youth Working Committee of Chinese Society of Aeronautics and Astronautics (CASS); Member of Academic Committee of the National Computational Fluid Dynamics Conference of China; National Organizing Committee of The 2023 Asia-Pacific International Symposium on Aerospace Technology; and will be the Chairmen of the 20th National Computational Fluid Dynamics Conference of China.

His research interests are supersonic aerodynamic design, large scale wind tunnel test technology, sonic boom prediction, etc. He has long been engaged in the research of basic frontier technologies of aerodynamics frontier technologies of aerodynamics. He has published more than 100 papers in journals and conferences, 20 invention patents, and edited 10 books. 

Title: Measurement and Identification of the Crossflow Stationary Wave for Straight-Sweep-Wing Based on Sublimation Method in a Large Scale Supersonic Cold Flow Wind Tunnel

Abstract:Aiming at the crossflow transition problem of supersonic swept wings, an experimental study on the measurement and identification of boundary layer stationary crossflow waves was carried out at Mach number 2.0 in AVIC ARI’s FL-60 tri-sonic wind tunnel. A 65° straight-sweep-wing model with simple airfoil geometry was designed to capture the crossflow transition phenomenon. The sublimation method for large scale cold supersonic wind tunnel was developed to acquire transition pattern. The stationary crossflow wave identification technology is based on image processing, and a vertical and horizontal decomposition method is established, and the quantitative characteristic information such as the vortex axis spacing and direction can be identified from high-resolution sublimation images. The experimental results show that the transition position caused by crossflow instability is closed to the leading edge for supersonic wings with large sweep angle at high Reynolds number, and the transition position moves upstream with the increase of the unit Reynolds number. The identified vortex axis spacing and direction are basically consistent with the Linear Stability Theory. The stationary disturbance wave information at different Reynolds numbers is compared and analyzed. It’s found that unit Reynolds number plays an important role in the selection and amplification of the unstable stationary modes with different wavelengths in the transition process.