Numerical Investigation on the Transition Flow around NLF Airfoil

A natural laminar flow (NLF) airfoil is designed to reduce drag by expanding areas. In-depth knowledge of transition performance essential for its aerodynamic design. The k-ω-γ-Reθ framework, which consists the SST k-ω turbulence model and γ-Reθ model, employed simulate transitional flows around an NLF wing RAE5243 airfoil. performances under various values turbulent intensity, temperature, angle attack, Mach number are simulated compared. results show that rise inflow intensity will promote earlier on both suction pressure sides. influence wall temperature limited. attack lead side but a later side. With number, happens zero positive negative attack. In addition, correlation onset locations with respect surface established based numerical results.