Aerodynamic performance of the locust wing in gliding mode at low Reynolds number

2016 ◽  
Vol 13 (2) ◽  
pp. 249-260 ◽  
Author(s):  
Jinwu Xiang ◽  
Jianxun Du ◽  
Daochun Li ◽  
Kai Liu
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Aerodynamic Performance ◽  
Low Reynolds ◽  
Locust Wing

A Computational Study on Airfoils at a Low Reynolds Number

2000 ◽  
Author(s):  
Ajit Pal Singh ◽  
S. H. Winoto ◽  
D. A. Shah ◽  
K. G. Lim ◽  
Robert E. K. Goh
Keyword(s):  
Reynolds Number ◽  
Computational Analysis ◽  
Computational Study ◽  
Low Reynolds Number ◽  
Micro Air Vehicles ◽  
Reynolds Numbers ◽  
Aerodynamic Performance ◽  
Low Reynolds Numbers ◽  
Study Results ◽  
Low Reynolds

Abstract Performance characteristics of some low Reynolds number airfoils for the use in micro air vehicles (MAVs) are computationally studied using XFOIL at a Reynolds number of 80,000. XFOIL, which is based on linear-vorticity stream function panel method coupled with a viscous integral formulation, is used for the analysis. In the first part of the study, results obtained from the XFOIL have been compared with available experimental data at low Reynolds numbers. XFOIL is then used to study relative aerodynamic performance of nine different airfoils. The computational analysis has shown that the S1223 airfoil has a relatively better performance than other airfoils considered for the analysis.

Comparative Investigation of Laminar Separation Bubble on a Wing at Low Reynolds Number

2020 ◽  
Vol 12 (3) ◽  
Author(s):  
M.P. Uthra ◽  
A. Daniel Antony
Keyword(s):  
Reynolds Number ◽  
Separation Bubble ◽  
Low Reynolds Number ◽  
Flow Characteristics ◽  
Suction Side ◽  
Aerodynamic Performance ◽  
Laminar Separation Bubble ◽  
Laminar Separation ◽  
Low Reynolds ◽  
Air Vehicles

Most admirable and least known features of low Reynolds number flyers are their aerodynamics. Due to the advancements in low Reynolds number applications such as Micro Air vehicles (MAV), Unmanned Air Vehicles (UAV) and wind turbines, researchers’ concentrates on Low Reynolds number aerodynamics and its effect on aerodynamic performance. The Laminar Separation Bubble (LSB) plays a deteriorating role in affecting the aerodynamic performance of the wings. The parametric study has been performed to analyse the flow around cambered, uncambered wings with different chord and Reynolds number in order to understand the better flow characteristics, LSB and three dimensional flow structures. The computational results are compared with experimental results to show the exact location of LSB. The presence of LSB in all cases is evident and it also affects the aerodynamic characteristics of the wing. There is a strong formation of vortex in the suction side of the wing which impacts the LSB and transition. The vortex structures impact on the LSB is more and it also increases the strength of the LSB throughout the span wise direction.

scholarly journals Aerodynamic Performance of Micro Aerial Wing Structures at Low Reynolds Number

2019 ◽  
Vol 11 (1) ◽  
pp. 107-120 ◽  
Author(s):  
Y. D. DWIVEDI ◽  
Vasishta BHARGAVA ◽  
P. M. V. RAO ◽  
Donepudi JAGADEESH
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Lift Coefficient ◽  
Reynolds Numbers ◽  
Aerodynamic Performance ◽  
Panel Method ◽  
Experiment Data ◽  
Wing Structures ◽  
Low Reynolds ◽  
Good Agreement

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.

scholarly journals Aerodynamic Performance of the NACA 2412 Airfoil at Low Reynolds Number

2016 ◽  
Author(s):  
John Matsson ◽  
John Voth ◽  
Connor McCain ◽  
Connor McGraw
Keyword(s):  
Reynolds Number ◽  
Low Reynolds Number ◽  
Aerodynamic Performance ◽  
Low Reynolds

Effect of mach number on high-subsonic and low-Reynolds-number flows around airfoils

2020 ◽  
Vol 34 (14n16) ◽  
pp. 2040112
Author(s):  
Jian-Hua Xu ◽  
Wen-Ping Song ◽  
Zhong-Hua Han ◽  
Zi-Hao Zhao
Keyword(s):  
Reynolds Number ◽  
Mach Number ◽  
Reverse Flow ◽  
Separation Bubble ◽  
Low Reynolds Number ◽  
Lift Coefficient ◽  
Aerodynamic Performance ◽  
Attack Angle ◽  
Low Reynolds ◽  
Flow Vortex

High-subsonic and low-Reynolds-number flow is a special aerodynamic problem associated with near space propellers and Mars aircrafts. The flow around airfoils and the corresponding aerodynamic performance are different from the incompressible flow at low-Reynolds-number, due to complex shock wave-laminar separation bubble interaction. The objective of this paper is to figure out the effect of Mach number on aerodynamic performance and special flow structure of airfoil. An in-house Reynolds-averaged Navier–Stokes solver coupled with [Formula: see text] transition model is employed to simulate the flows around the E387 airfoil. The results show that the lift slope is larger than [Formula: see text] in the linear region. No stall occurs even at an attack angle of [Formula: see text]. With increase of Mach number, lift coefficient decreases when attack angle is below [Formula: see text]. However, once the angle of attack exceeds [Formula: see text], higher Mach number corresponds to higher lift coefficient. In addition, the strength and number of shock waves are very sensitive to Mach number. With increase of Mach number, the region of reverse flow vortex near transition location becomes smaller and finally disappears, while a new reverse flow vortex appears near the trailing edge and becomes larger.

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