scholarly journals Horizontal Wind Effect on the Aerodynamic Performance of Coaxial Tri-Rotor MAV

2020 ◽  
Vol 10 (23) ◽  
pp. 8612
Author(s):  
Yao Lei ◽  
Yiqiang Ye ◽  
Zhiyong Chen
Keyword(s):  
Wind Tunnel ◽  
Power Consumption ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
Horizontal Wind ◽  
Wind Effect ◽  
Rotor Speed ◽  
Wind Tunnel Experiments ◽  
Air Vehicle ◽  
Power Loading

The coaxial Tri-rotor micro air vehicle (MAV) is composed of three coaxial rotors where the aerodynamic characteristics of is complicated in flight especially when the wind effect is introduced. In this paper, the hovering performance of a full-scale coaxial Tri-rotor MAV is analyzed with both the simulations and wind tunnel experiments. Firstly, the wind effect on the aerodynamic performance of coaxial Tri-rotor MAV is established with different rotor speed (1500–2300 rpm) and horizontal wind (0–4 m/s). Secondly, the thrust and power consumption of coaxial Tri-rotor (L/D = 1.6) were obtained with low-speed wind tunnel experiments. Furthermore, the streamline distribution, pressure distribution, velocity contour and vortex distribution with different horizontal wind conditions are obtained by numerical simulations. Finally, combining the experiment results and simulation results, it is noted that the horizontal wind may accelerate the aerodynamic coupling, which resulting in the greater thrust variation up to 9% of the coaxial Tri-rotor MAV at a lower rotor speed. Moreover, the aerodynamic performance is decreased with more power consumption at higher rotor speed where the wind and the downwash flow are interacted with each other. Compared with no wind flow, the shape of the downwash flow and the deformation of the vortex affect the power loading and figure of metric accordingly.

scholarly journals The aerodynamic performance of Non-planar hex-rotors aircraft subjected the horizontal wind disturbanceLei yao1,2* Ma Chensong1 Feng Zhicheng1

2021 ◽  
Author(s):  
Lei yao ◽  
Ma Chensong ◽  
Feng Zhicheng
Keyword(s):  
Wind Speed ◽  
Power Consumption ◽  
Tilt Angle ◽  
Wind Tunnel Test ◽  
Aerodynamic Performance ◽  
Horizontal Wind ◽  
Horizontal Wind Speed ◽  
Power Loading ◽  
Experimental Values ◽  
Cfd Method

Abstract The non-planar hex-rotor aircraft mentioned in this article can change its flight status by simply changing the tilt angle of the rotor. In this paper, mainly studied the best aerodynamic performance of a non-planar hex-rotor aircraft under the influence of horizontal wind (0m/s, 2.5m/s and 4m/s). Firstly, the rotation speed of the rotor is a fixed value (2200r/min) in the low-speed wind tunnel test, the horizontal wind speed and the tilt angle of the rotor are variable values, the thrust, power consumption and power loading(PL) values of the aircraft are obtained. Secondly, the computational fluid dynamics(CFD) method is used to simulate the aerodynamic performance of a non-planar hex-rotors aircraft when subjected to a horizontal wind to obtain the simulation results. Finally, comparing the experimental values and the simulation values, it is found that the horizontal speed has a greater impact on the thrust and power consumption of the non-planar hex-rotor aircraft. From the change of PL values, it is concluded that the horizontal wind speed is 0m/s, 2.5m/s, 4m/s, the best inclination angle is 10°, 30°and 50°, and the strongest anti-wind performance.

scholarly journals Effects of Wind Disturbance on the Aerodynamic Performance of a Quadrotor MAV during Hovering

2021 ◽  
Vol 2021 ◽  
pp. 1-13
Author(s):  
Yao Lei ◽  
Yiyong Huang ◽  
Hengda Wang
Keyword(s):  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
Vertical Wind ◽  
Horizontal Wind ◽  
Wind Disturbance ◽  
Power Variation ◽  
Quadrotor Aircraft ◽  
Spacing Ratio ◽  
Power Loading ◽  
Vertical Winds

Wind disturbance could render thrust and power variation or even causing roll which is difficult to maintain a steady flight in gust especially when the horizontal or vertical wind is involved. In this paper, the horizontal wind and vertical wind are presented to study the influence of wind disturbance on aerodynamic characteristics of the quadrotor aircraft in hovering by experiments and numerical simulations. First, the simplified aerodynamic model with the wind disturbance was analyzed in detail. Also, the low-speed wind tunnel tests were performed to obtain the thrust and power variation of the quadrotor aircraft with rotor spacing ratio s = 1.1 -1.8 in both horizontal and vertical winds of 0-5 m/s with the rotational speed ranging from 1500 to 2300 rpm. Finally, the simulations are performed by utilizing the Computational Fluid Dynamics (CFD) software ANSYS to study the flow field distribution of quadrotor with the influence of the wind disturbance. The comparison between experimental results and simulation results shows that the quadrotor achieves better aerodynamic performance with larger thrust and smaller power consumption at rotor spacing ratio s = 1.8 . Additionally, the quadrotor can effectively resist the horizontal wind disturbance, which will bring larger power loading for the quadrotor, especially at 2.5 m/s. However, the vortices near blade-tip move upwards and deform with the influence of vertical wind, resulting in the reduction of thrust and aerodynamic performance of the quadrotor.

scholarly journals Aerodynamic Performance of Hex-Rotor UAV Considering the Horizontal Airflow

2019 ◽  
Vol 9 (22) ◽  
pp. 4797
Author(s):  
Yao Lei ◽  
Mingxin Cheng
Keyword(s):  
Wind Tunnel ◽  
Numerical Simulations ◽  
Aerodynamic Performance ◽  
Wind Tunnel Experiments ◽  
Low Speed ◽  
Pressure Distributions ◽  
Hover Performance ◽  
Power Loading ◽  
Aerial Vehicle ◽  
Low Speed Wind Tunnel

In this paper, the aerodynamic performance of a Hex-rotor unmanned aerial vehicle (UAV) with different rotational speeds (1500–2300 RPM) considering the horizontal airflow conditions is analyzed by both simulations and experiments. A low-speed wind tunnel experiments platform is applied to measure the thrust, torque, and power consumption of a Hex-rotor UAV with different rotational speeds in horizontal airflow, which varied from 0 m/s–4 m/s. First, this paper introduces the effect of horizontal airflow on a UAV. Then, the low-speed wind tunnel experiments were carried out on a Hex-rotor UAV (D/L = 0.56) with different horizontal velocities to determine the hover performance. Finally, numerical simulations were obtained with the streamline distributions, pressure distributions, velocity contour, and vortex distributions at different horizontal airflow conditions to describe the aerodynamic interference effect of different horizontal airflows. Combined with the experimental results and numerical simulations results, the horizontal airflow proved to have a significant influence on the aerodynamic performance of the Hex-rotor UAV with an increase in thrust and power. Indeed, the streamlines in the flow field were coupled to each other at the presence of the incoming airflow. Especially when the incoming airflow was larger, the Hex-rotor UAV could properly use low-speed flight to maintain high power loading. Finally, it is inferred that the aerodynamic performance of the Hex-rotor UAV is also related to the movement and deformation of the vortex at the tip of the rotor.

scholarly journals Aerodynamic Characteristics of Shark Scale-Based Vortex Generators upon Symmetrical Airfoil

Energies ◽  
2021 ◽  
Vol 14 (7) ◽  
pp. 1808
Author(s):  
S. Arunvinthan ◽  
V.S. Raatan ◽  
S. Nadaraja Pillai ◽  
Amjad A. Pasha ◽  
M. M. Rahman ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
Vortex Generators ◽  
Geometrical Parameters ◽  
Flow Properties ◽  
Wind Tunnel Experiments ◽  
Maximum Coefficient ◽  
Effective Use ◽  
Naca 0015

A series of wind tunnel tests were carried out to determine the effect of shark scale-based vortex generators (SSVG) on a NACA 0015 symmetrical airfoil's aerodynamic characteristics. Three different sets of SSVG with varying geometrical parameters, such as chord length, amplitude, and wavelength, were designed and fabricated using 3D printing. The SSVG models were blended to the baseline NACA 0015 symmetrical airfoil. The wind tunnel experiments were performed over the test airfoil mounted with different sets of SSVG at various angles of attack, ranging from 0° to 24° in increments of 3°, and operating in the range of Re = 2 × 105. The results revealed that the SSVG blended test airfoil reduced the drag and increased the maximum coefficient of lift (CLmax), thereby enhancing the overall aerodynamic performance. The SSVG offered noteworthy aerodynamic benefits by effectively altering the flow and causing significant spanwise variation in the flow properties. Additionally, attempts were made to identify the optimum chordwise location to blend the SSVG for effective use.

scholarly journals Aerodynamic Characteristics of a Micro Multi-Rotor Aircraft with 12 Rotors Considering the Horizontal Wind Disturbance

2020 ◽  
Vol 10 (20) ◽  
pp. 7387
Author(s):  
Yao Lei ◽  
Wenjie Yang ◽  
Hengda Wang
Keyword(s):  
Power Consumption ◽  
Micro Air Vehicles ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
Horizontal Wind ◽  
Wind Disturbance ◽  
Wind Speeds ◽  
Hover Performance ◽  
Blade Tip ◽  
Cfd Method

Wind disturbance posed difficulties for the stability of the micro air vehicles (MAVs) with attitude variation. In this paper, the aerodynamic performance of a MAV with six coaxial rotor pairs considering the horizontal wind is investigated by both experiments and numerical simulations. First, the effect of the horizontal wind on the multi-rotor aircraft is analyzed in detail. Then, low-speed wind tunnel tests were performed to obtain the thrust and power consumption and the aerodynamic performance of the multi-rotor aircraft (l/D = 1.2 and h/D = 0.19) with the rotational speed of 1500–2300 r/min in the horizontal wind ranged from 0 to 5 m/s. Finally, the distribution of streamline, the pressure of the blade tip, and the velocity and the vortices in the flow field of a multi-rotor aircraft with horizontal wind disturbance, were simulated and studied using the computational fluid dynamics (CFD) method. Through the comparison of experimental results and simulation results, it can be seen that the horizontal wind disturbance will increase power consumption to weaken the aerodynamic performance at higher rotor speeds. However, larger thrust and better hover performance are obtained at lower rotational speeds with good wind resistance. Additionally, due to the mutual induction between rotor wakes, the interactions of downwash flows become more intense at higher rotational speeds or larger wind speeds where the vortexes at the blade tip deformed and moved along with the wind.

Numerical Simulations and Wind Tunnel Experiments of Aerodynamic Characteristics on Waverider with Orbiter

2017 ◽  
Vol 2017.70 (0) ◽  
pp. 502
Author(s):  
Tomoki UZAKI ◽  
Tomoyuki MUTA ◽  
Nobuyuki TSUBOI ◽  
Yusuke MARU ◽  
Kazuhisa FUJITA
Keyword(s):  
Wind Tunnel ◽  
Numerical Simulations ◽  
Aerodynamic Characteristics ◽  
Wind Tunnel Experiments

scholarly journals Implementation of a Hybrid Electro-Active Actuated Morphing Wing in Wind Tunnel

2017 ◽  
Vol 260 ◽  
pp. 85-91 ◽  
Author(s):  
Gurvan Jodin ◽  
Johannes Scheller ◽  
Eric Duhayon ◽  
Jean François Rouchon ◽  
Marianna Braza
Keyword(s):  
Wind Tunnel ◽  
Shape Memory ◽  
Low Frequency ◽  
Aerodynamic Performance ◽  
Point Of View ◽  
Morphing Wing ◽  
Wind Tunnel Experiments ◽  
Trailing Edge ◽  
Actuation System ◽  
Hybrid Actuation

Amongst current aircraft research topics, morphing wing is of great interest for improving the aerodynamic performance. A morphing wing prototype has been designed for wind tunnel experiments. The rear part of the wing - corresponding to the retracted flap - is actuated via a hybrid actuation system using both low frequency camber control and a high frequency vibrating trailing edge. The camber is modified via surface embedded shape memory alloys. The trailing edge vibrates thanks to piezoelectric macro-fiber composites. The actuated camber, amplitude and frequency ranges are characterized. To accurately control the camber, six independent shape memory alloy wires are controlled through nested closed-loops. A significant reduction in power consumption is possible via this control strategy. The effects on flow via morphing have been measured during wind tunnel experiments. This low scale mock-up aims to demonstrate the hybrid morphing concept, according to actuator capabilities point of view as well as aerodynamic performance.

scholarly journals Effect of Ground Proximity on Aerodynamic Characteristics of NACA 4412 Airfoil.

2022 ◽  
pp. 96-104
Author(s):  
Aditi Deekshita Pallay ◽  
Abdul Wahab ◽  
Akhil Shesham ◽  
Y D Dwivedi
Keyword(s):  
Wind Tunnel ◽  
Flow Behavior ◽  
Ground Effect ◽  
Aerodynamic Characteristics ◽  
Aerodynamic Performance ◽  
Vital Role ◽  
Ground Clearance ◽  
Induced Drag ◽  
Good Accordance ◽  
Low Speed Wind Tunnel

Ground effect plays a vital role in modulating the flow behavior over any streamlined body. The most widely used wing-in ground effect (WIG) aircrafts and seaplanes utilize this phenomenon in order to enhance the aerodynamic performance during the landing and take-off phases of flight. This paper investigates the aerodynamics of ground effect on a NACA 4412 rectangular wing without end plates. The experiment was conducted in a low-speed wind tunnel at Re=2×105 for the ground clearance of 1 and 0.5 of the chord, measured from the maximum thickness position on the airfoil. The pressure distribution over the chord length was recorded for α=3° and 6° to verify the effect of ground clearance during takeoffs. The results have shown to be in good accordance with the literature, as the coefficient of lift augmented with increase in ground proximity and the induced drag was minimized.

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