Aerodynamic Performance of Micro Aerial Wing Structures at Low Reynolds Number

• Published in: INCAS bulletin Vol. 11; no. 1; pp. 107 - 120
• Main Authors: DWIVEDI, Y. D., BHARGAVA, Vasishta, RAO, P. M. V., JAGADEESH, Donepudi
• Format: Journal Article
• Language: English
• Published: Bucharest INCAS - National Institute for Aerospace Research "Elie Carafoli" 05.03.2019; National Institute for Aerospace Research “Elie Carafoli” - INCAS
• Subjects: Aerodynamic coefficients; Aerodynamics; Angle of attack; Biology; Computational fluid dynamics; Corrugated airfoil; Drag coefficient; Drag coefficients; Experiments; Fluid flow; Fluids; Geometry; Incompressible flow; Insects; Lift coefficient; Methods; Panel method; Panel method (fluid dynamics); Pressure; Researchers; Reynolds number; Studies; Unmanned aerial vehicles; Vehicles; Velocity; Wind tunnels; United States > US
• ISSN: 2066-8201; 2247-4528
• DOI: 10.13111/2066-8201.2019.11.1.8

Corrugations are folds on a surface as found on wings of dragon fly insects. Although they fly at relatively lower altitudes its wings are adapted for better aerodynamic and aero-elastic characteristics. In the present work, three airfoil geometries were studied using the 2-D panel method to evaluate the aerodynamic performance for low Reynolds number. The experiments were conducted in wind tunnel for incompressible flow regime to demonstrate the coefficients of lift drag and glide ratio at two Reynolds numbers 1.9x104 and 1.5x105 and for angles of attack ranging between 00 and 160. The panel method results have been validated using the current and existing experiment data as well as with the computational work from cited literature. A good agreement between the experimental and the panel methods were found for low angles of attack. The results showed that till 80 angle of attack higher lift coefficient and lower drag coefficient are obtainable for corrugated airfoils as compared to NACA 0010. The validation of surface pressure coefficients for all three airfoils using the panel method at 40 angles of attack was done. The contours of the non-dimensional pressure and velocity are illustrated from -100 to 200 angles of attack. A good correlation between the experiment data and the computational methods revealed that the corrugated airfoils exhibit better aerodynamic performance than NACA 0010.