TY - GEN
T1 - Low Reynolds number airfoil testing in a Mars Wind Tunnel
AU - Anyoji, Masayuki
AU - Nose, Kei
AU - Ida, Shingo
AU - Numata, Daiju
AU - Nagai, Hiroki
AU - Asai, Keisuke
PY - 2010/12/2
Y1 - 2010/12/2
N2 - The aerodynamic characteristics of a 5% flat plate and NACA0012-34 airfoil in low Reynolds number (Re=0.43×104∼4.1×10 4) and high subsonic flow (M=0.1∼0.6) were investigated in the Mars Wind Tunnel (MWT) at Tohoku University. A two-component balance system and Pressure-Sensitive Paint (PSP) technique have been developed to measure the lift and drag forces and pressure profiles on the model. For the flat plate, Mach number effect does not have much effect on its aerodynamic performance while Reynolds number affects the lift slope and the drag characteristics. On the contrary, for NACA0012-34 airfoil, both Reynolds and Mach number effects become more prominent. The lift curves are highly nonlinear and the drag polars are affected by behaviors of a laminar separation bubble in trans-critical condition. A comparison of the results obtained at different Mach numbers has suggested that the compressibility has an effect to stabilize separated shear layer. It has been verified by this experiment that the MWT can offer a unique capability to investigate airfoil performance in low Reynolds number and high Mach number flow.
AB - The aerodynamic characteristics of a 5% flat plate and NACA0012-34 airfoil in low Reynolds number (Re=0.43×104∼4.1×10 4) and high subsonic flow (M=0.1∼0.6) were investigated in the Mars Wind Tunnel (MWT) at Tohoku University. A two-component balance system and Pressure-Sensitive Paint (PSP) technique have been developed to measure the lift and drag forces and pressure profiles on the model. For the flat plate, Mach number effect does not have much effect on its aerodynamic performance while Reynolds number affects the lift slope and the drag characteristics. On the contrary, for NACA0012-34 airfoil, both Reynolds and Mach number effects become more prominent. The lift curves are highly nonlinear and the drag polars are affected by behaviors of a laminar separation bubble in trans-critical condition. A comparison of the results obtained at different Mach numbers has suggested that the compressibility has an effect to stabilize separated shear layer. It has been verified by this experiment that the MWT can offer a unique capability to investigate airfoil performance in low Reynolds number and high Mach number flow.
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M3 - Conference contribution
AN - SCOPUS:78649480758
SN - 9781617389221
T3 - 40th AIAA Fluid Dynamics Conference
BT - 40th AIAA Fluid Dynamics Conference
T2 - 40th AIAA Fluid Dynamics Conference
Y2 - 27 June 2010 through 30 June 2010
ER -