Three acceleration sensors are used to obtain the vibration data.Findings\nThe results show that the increase in the amplitude of the vibration is directly related to the decrease in lift. These findings indicate that this approach could be beneficial in detecting stall on airfoil-type structures....
The experimental data is for an airfoil with a trip wire, which forces the boundary layer to be completely turbulent.[1] This corresponds to the Fluent model, which has an active turbulence model over the complete airfoil. Note that the calculated drag coefficient is somewhat higher than the ...
First, experimental and numerical methods used to investigate the flow and lift force of a NACA0012 airfoil in the low Reynolds number range Re∈[50,000:140,000] are described. Second, predictions from low and high-fidelity simulations are compared with experimental data for the lowest Reynolds...
This research paper presents the design and analysis of a NACA 0012 airfoil with a circular dent of 30 mm depth on its upper surface. The objective of this study is to investigate the effect of the dent on the airfoil's aerodynamic performance. The airfoil's geometry was modeled using a ...
Calculations of ice shapes and the resulting drag increases are presented for experimental data on an NACA 0012 airfoil. They were made with a combination ... J Shin,B Berkowitz - 《Journal of Aircraft》 被引量: 109发表: 1994年 Ice shapes and the resulting drag increase for a NACA 0012 ...
Experimental flutter boundaries are presented for a rigid semispan model (NACA 0012 airfoil section) mounted on a flexible mount system. Also, steady and unsteady pressure measurements taken at the flutter condition are presented. The pressure data were acquired over the entire model chord located ...
the old NACA 0018 airfoil as a balance between aerodynamic performance and structural integrity. It appears however that, despite the many applications, information on the performance of this airfoil at the appropriate Reynolds numbers and test conditions is non- ...
Two low speed aerofoil design computer programs have been evaluated over a Reynolds number range of 2 × 105 to 1 × 106, using experimental data obtained from Cranfield’s 8′ × 6′ low speed wind tunnel, for a NACA 643–418...
Earlier research for theNACA643-618 airfoil has shown that lift-curve and stall behavior change noticeablywhennthe chord Reynolds number is reduced signica... AGF Fasel - 《Aiaa Journal》 被引量: 0发表: 2010年 Theoretical and Experimental Data for a Number of NACA 6A-Series Airfoil Sections ...
numerical simulations are compared with experimental data .Periodic vortex shedding behind airfoil tail is obtained using unsteady numerical simulation .Time-averaged computational results obtained by un-steady method are batter then steady computational results .%对NACA4412翼型低速绕流进行了定常/非定常数值...