03.3 - Basic Fluid Dynamics and Flow Control
SUBSONIC WIND TUNNEL SMALL RIBLETS DRAG REDUCTION EXPERIMENT ON C919 FUSELAGE MODEL
H.W. Wang¹, Z. Huang¹, M.L. Yuan¹, X.H. Li¹, M. Zhang, Shanghai Aircraft Design and Research Institute, China; ¹China Academy of Aerospace Aerodynamics, China
A micron scale of small riblets film suitable for subsonic wind tunnel turbulent flow field was designed for the C919 fuselage model and compared with the smooth film. According to balance, PIV and fluorescence oil film test, the total drag coefficient was reduced 1%-2%, and the turbulence intensity and kinetic energy were all reduced, and the relative skin friction amplitude was also reduced.