Numerical Simulation on the Effect of Angle of Attack on Aerodynamic Forces about Flapping Wing in Hovering Motion

Hummingbirds and some insects exhibit “Figure-8” flapping motion that allows them to go through a variety of maneuvers including hovering. Understanding the flight characteristics of Figure-8 flapping motion can potentially yield the foundation of flapping wing UAVs that can experience similar maneuverability. In this paper, a mathematical model of the dynamic and aerodynamic forces associated with Figure-8 motion generated by a spherical four bar mechanism is developed. For validation, a FWMAV prototype with the wing attached to a coupler point and driven by a DC servo motor is created for experimental testing. Wind tunnel testing is conducted to determine the coefficients of flight and the effects of dynamic stall. The wing is driven at speeds up to 12.25 Hz with results compared to that of the model. The results indicate good correlation between mathematical model and experimental prototype.

Download Full-text

NUMERICAL SIMULATION OF AIRFLOW AROUND VEHICLE MODELS

Vietnam Journal of Science and Technology ◽

10.15625/2525-2518/56/3/10498 ◽

2018 ◽

Vol 56 (3) ◽

pp. 370

Author(s):

Nguyen Van Thang ◽

Ha Tien Vinh ◽

Bui Dinh Tri ◽

Nguyen Duy Trong

Keyword(s):

Numerical Simulation ◽

Kinetic Energy ◽

Three Dimensional ◽

Aerodynamic Characteristics ◽

Aerodynamic Forces ◽

Dissipation Energy ◽

Ansys Fluent ◽

Car Model ◽

Airflow Field ◽

Fluent Software

This article carries out the numerical simulation of airflow over three dimensional car models using ANSYS Fluent software. The calculations have been performed by using realizable k-e turbulence model. The external airflow field of the simplified BMV M6 model with or without a wing is simulated. Several aerodynamic characteristics such as pressure distribution, velocity contours, velocity vectors, streamlines, turbulence kinetic energy and turbulence dissipation energy are analyzed in this study. The aerodynamic forces acting on the car model is calculated and compared with other authors.

Download Full-text

Numerical simulation of the flow around a flapping-wing micro air vehicle in free flight

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410018800161 ◽

2018 ◽

pp. 095441001880016 ◽

Cited By ~ 2

Author(s):

M Moriche ◽

E Hernández-Hurtado ◽

O Flores ◽

M García-Villalba

Keyword(s):

Numerical Simulation ◽

Flapping Wing ◽

Micro Air Vehicle ◽

Free Flight ◽

Air Vehicle

Download Full-text

Aerodynamic effects of bio-inspired corrugated wings on gliding and hovering performances

Proceedings of the Institution of Mechanical Engineers Part C Journal of Mechanical Engineering Science ◽

10.1177/0954406220917995 ◽

2020 ◽

pp. 095440622091799

Author(s):

Haibin Xuan ◽

Jun Hu ◽

Yong Yu ◽

Jiaolong Zhang

Keyword(s):

Inclination Angle ◽

Fluid Dynamic ◽

Angle Of Attack ◽

Aerodynamic Forces ◽

Limited Effect ◽

Gliding Flight ◽

Significant Difference ◽

Inclination Angles ◽

Underlying Mechanisms ◽

Lift And Drag

Recently, numerous studies have been conducted to clarify the effects of corrugation wing on aerodynamic performances. The effects of the corrugation patterns and inclination angles were investigated using computational fluid dynamic method in gliding and hovering flight at Reynolds numbers of order 104. The instantaneous aerodynamic forces and the vorticity field around the wing models were provided to research the underlying mechanisms of aerodynamic effects of corrugated wing models. The findings can be concluded as follows: (1) the corrugation patterns have different effects on aerodynamic performance. The effect of noncamber corrugated wing is to decrease the lift and increase drag compared with a flat-plate when the angle of attack is less than 25° during gliding flight. The corrugated wing with a camber (corrug-2) after the valleys enhances the aerodynamic forces when angle of attack is higher than 35°. The valley inclination angle has limited effect on aerodynamic forces in gliding flight. (2) The lift forces of different corrugation patterns show significantly asymmetric during the upstroke and downstroke. The main reason leads to this phenomenon is the case that two sides of the corrugated wings are not symmetric around the pitching axis. The corrugated wing with only two valleys (corrug-1) changes the lift and drag very slightly. Corrug-2 produces larger peak during downstroke and smaller peak during upstroke. The increase in the inclination angle has limited effect on the aerodynamic forces. The possible reason for these small aerodynamic effects might be that the corrugated wings are smoothed by small vortices trapped in valleys. The main reason for the significant difference between plate and corrug-2 is that the recirculating vortices trapped in the saddle and hump reduce the pressure above the wing surface.

Download Full-text

Numerical Simulation for Engine/Airframe Interaction Effects of the BWB300 on Aerodynamic Performances

International Journal of Aerospace Engineering ◽

10.1155/2019/1072196 ◽

2019 ◽

Vol 2019 ◽

pp. 1-15 ◽

Cited By ~ 1

Author(s):

Gang Yu ◽

Dong Li ◽

Yue Shu ◽

Zeyu Zhang

Keyword(s):

Numerical Simulation ◽

High Speed ◽

Separated Flow ◽

Simulation Method ◽

Interaction Effects ◽

Surface Flow ◽

Concept Design ◽

Aerodynamic Forces ◽

Low Speed ◽

Aerodynamic Performances

The engine/airframe interaction effects of the BWB300 on aerodynamic performances were analyzed by using the numerical simulation method. The BWB300 is a 300-seat Blended Wing Body airplane designed by the Airplane Concept Design Institute of Northwestern Polytechnical University. The engine model used for simulation was simplified as a powered nacelle. The results indicated the following: at high speed, although the engine/airframe interaction effects on the aerodynamic forces were not significant, the airframe’s upper surface flow was greatly changed; at low speed, the airframe’s aerodynamic forces (of the airplane with/without the engine) were greatly different, especially at high attack angles, i.e., the effect of the engine suction caused the engine configuration aerodynamic forces of the airframe to be bigger than those without the engine; and the engine’s installation resulting in the different development of flow separation at the airframe’s upper surface caused greater obvious differences between the 2 configurations at high angles and low speed. Moreover, at low-speed high attack angles, the separated flow from the blended area caused serious distortion at the fan inlet of the engine.

Download Full-text

Numerical Simulation of Flow and Determination of Aerodynamic Forces in the Balanced Control Valve

EPJ Web of Conferences ◽

10.1051/epjconf/20134501062 ◽

2013 ◽

Vol 45 ◽

pp. 01062 ◽

Cited By ~ 1

Author(s):

R. Matas ◽

F. Straka ◽

M. Hoznedl

Keyword(s):

Numerical Simulation ◽

Control Valve ◽

Aerodynamic Forces

Download Full-text

The Hinge Moment Optimization of Rudder Base on CFD Numerical Simulation

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.397-400.218 ◽

2013 ◽

Vol 397-400 ◽

pp. 218-221

Author(s):

Nan Zhang ◽

Yue Zhang

Keyword(s):

Numerical Simulation ◽

Angle Of Attack ◽

Special Design ◽

Optimization Program ◽

Airfoil Optimization ◽

Structured Grid ◽

Simulation Calculation ◽

Cfd Numerical Simulation ◽

Grid Division ◽

Rudder Angle

The paper introduce structured grid division, use CFD numerical simulation and FLUNET software to conduct the simulation calculation for the hinge moment of rudder. To illustrate the problem, we select two unused plane airfoil An axis-symmetric rudder, one for the special design of the plane rudder. Calculated at 0.4 ~ 1.8Ma, different rudder angle, angle of attack different hinge moment value, and compare them ultimately come to a flat airfoil optimization program, making the steering hinge moment to meet the indicators proposed.

Download Full-text