Physical law and modeling of compressible separated flows using high-fidelity spatio-temporal large-scale data

2023 Fiscal Year Final Research Report

• Project/Area Number: 21H01523
• Research Category: Grant-in-Aid for Scientific Research (B)
• Allocation Type: Single-year Grants
• Section: 一般
• Review Section: Basic Section 24010:Aerospace engineering-related
• Research Institution: Tohoku University
• Principal Investigator: Kawai Soshi 東北大学, 工学研究科, 教授 (40608816)
• Project Period (FY): 2021-04-01 – 2024-03-31
• Keywords: 乱流境界層 / 高レイノルズ数流れ / 圧縮性流体 / LES / データ駆動科学

Outline of Final Research Achievements

This study investigated a wall modeling in large-eddy simulation (LES) that enables high-fidelity simulations of compressible separated turbulent boundary layers with shock waves and wall heat fluxes at high Reynolds numbers, which have a significant impact on aerodynamics and the safety of aircraft and rockets. Based on large-scale direct numerical simulation databases, the details of the compressible flows with shock waves and wall heat fluxes are analyzed, and a wall model is developed based on the obtained knowledge. Using the wall model, low-frequency self-excited oscillation phenomena caused by shock waves and separated turbulent boundary layers in an over-expanded nozzle with wall heat flux at a high Reynolds number were investigated to validate the developed wall-modeled LES.

Free Research Field

航空宇宙工学

Academic Significance and Societal Importance of the Research Achievements

航空機やロケット開発の設計上流段階から信頼できる機体設計を実現するため，高忠実なLESの設計開発への展開に対する期待が近年大きくなってきている． LESを設計開発に展開するためには，航空宇宙分野で扱う必要がある10の7乗レベルの高レイノルズ数条件における衝撃波や壁面熱流束を伴う圧縮性乱流境界層剥離流れを予測可能とするLES技術（壁面モデルLES）の確立が不可欠であり，当該研究分野に貢献することを目指して研究を推進した．また本研究成果は，航空宇宙分野に限らず，衝撃波や壁面熱流束を伴う幅広い工学分野の高レイノルズ数流れを伴う流体解析に対する波及効果も期待できると考えている．