Aerodynamical Improvement of Delta Wing and Flapping Wing

2015 ◽  
Author(s):  
Tadateru Ishide ◽  
Kazuya Naganuma ◽  
Shinsuke Seiji ◽  
Hiroyuki Ishikawa ◽  
Ryo Fujii ◽  
...  
Keyword(s):  
Force Measurement ◽  
Delta Wing ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Flapping Wing ◽  
Fluid Force ◽  
Unmanned Air Vehicle ◽  
Wide Range ◽  
Air Vehicle ◽  
Piv Analysis

Recently, various studies of Micro Air Vehicle (MAV) and Unmanned Air Vehicle (UAV) have been reported from wide range points of view. The aim of this study are researching the aerodynamic improvement of delta wing and flapping wing in low Reynold’s number region to develop an applicative these air vehicle. Various configurations of Leading Edge Flap (LEF) are used to enhance the aerodynamic characteristics in the delta wing. The six kind of elliptical wings made of stainless steel are used in the flapping wing. The effects of flapping amplitude and wing configuration regarding the aerodynamic characteristics are investigated in detail. The fluid force measurement by six component load cell and PIV analysis are performed as the experimental method. In the flapping wing experiment, the simultaneous measuring of the fluid force measurement and PIV analysis is tried by using the trigger signal from the encoder attached to the flapping model. The relations between the aerodynamic superiority and the vortex behavior around the models are demonstrated.

Recent progress in flapping wings for micro aerial vehicle applications

2020 ◽  
pp. 095440622091742
Author(s):  
Naeem Haider ◽  
Aamer Shahzad ◽  
Muhammad Nafees Mumtaz Qadri ◽  
Syed Irtiza Ali Shah
Keyword(s):  
Leading Edge ◽  
Flapping Wing ◽  
Flapping Wings ◽  
Structural Flexibility ◽  
Micro Aerial Vehicles ◽  
Flexible Wings ◽  
Performance Variables ◽  
Aerial Vehicles ◽  
Wide Range ◽  
Wing Geometry

Micro aerial vehicles using flapping wings are under investigation, as an alternative to fixed-wing and rotary-wing micro aerial vehicles. Such flapping-wing vehicles promise key potential advantages of high thrust, agility, and maneuverability, and have a wide range of applications. These applications include both military and commercial domains such as communication relay, search and rescue, visual reconnaissance, and field search. With the advancement in the computational sciences, developments in flapping-wing micro aerial vehicles have progressed exponentially. Such developments require a careful aerodynamic and aeroelastic design of the flapping wing. Therefore, aerodynamic tools are required to study such designs and configurations. In this paper, the role of several parameters is investigated, including the types of flapping wings, the effect of the kinematics and wing geometry (shape, configuration, and structural flexibility) on performance variables such as lift, drag, thrust, and efficiency in various modes of flight. Kinematic variables have a significant effect on the performance of the flapping wing. For instance, a high flap amplitude and pitch rotation, which supports the generation of the strong leading-edge vortex, generates higher thrust. Likewise, wing shape, configuration, and structural flexibility are shown to have a large impact on the performance of the flapping wing. The wing with optimum flexibility maximizes thrust where highly flexible wings lead to performance degradation due to change in the effective angle of attack. This study shows that the development of the flexible flapping wing with performance capabilities similar to those of natural fliers has not yet been achieved. Finally, opportunities for additional research in this field are recommended.

scholarly journals Serve Ball Trajectory Characteristics of Different Volleyballs and Their Causes

Proceedings ◽  
2020 ◽  
Vol 49 (1) ◽  
pp. 146
Author(s):  
Takehiro Tamaru ◽  
Shinichiro Ito ◽  
Masaki Hiratsuka
Keyword(s):  
High Speed ◽  
Trajectory Analysis ◽  
Force Measurement ◽  
Aerodynamic Characteristics ◽  
Flight Trajectory ◽  
Fluid Force ◽  
Spin Speed ◽  
Trajectory Measurement ◽  
Ball Trajectory ◽  
Effective Service

Volleyball is a sport that starts with a serve, so effective service is essential to win the game. The trajectory of the ball is complicatedly affected by the fluid force, which depends on the speed, spin speed, and panel shape. To understand the aerodynamic characteristics of the ball and to propose an ideal serve method, we measured the fluid force and flight trajectory. The fluid force applied to the ball was measured at a wind speed of 4–30 m/s in the wind tunnel. The fluid force on the ball was strongly dependent on the ball type and orientation of the panel. In the flight trajectory measurement, the trajectory of the ball was measured using a high-speed camera under controlled speed and spin speed using a shotting machine. The effect of the panel orientation shown by the fluid force measurement was consistent with the results of the trajectory analysis, clarifying the importance of the panel orientation in serving.

The leading-edge vortex and aerodynamics of insect-based flapping-wing micro air vehicles

2009 ◽  
Vol 113 (1142) ◽  
pp. 253-262 ◽  
Author(s):  
P. C. Wilkins ◽  
K. Knowles
Keyword(s):  
Entire Range ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Micro Air Vehicles ◽  
Reynolds Numbers ◽  
Flapping Wing ◽  
Computational Method ◽  
Leading Edge Vortex ◽  
Air Vehicle ◽  
Edge Vortex

AbstractThe aerodynamics of insect-like flapping are dominated by the production of a large, stable, and lift-enhancing leading-edge vortex (LEV) above the wing. In this paper the phenomenology behind the LEV is explored, the reasons for its stability are investigated, and the effects on the LEV of changing Reynolds number or angle-of-attack are studied. A predominantly-computational method has been used, validated against both existing and new experimental data. It is concluded that the LEV is stable over the entire range of Reynolds numbers investigated here and that changes in angle-of-attack do not affect the LEV’s stability. The primary motivation of the current work is to ascertain whether insect-like flapping can be successfully ‘scaled up’ to produce a flapping-wing micro air vehicle (FMAV) and the results presented here suggest that this should be the case.

20506 The Aerodynamic Characteristics of a Delta Wing with Leading Edge Flaps

2014 ◽  
Vol 2014.20 (0) ◽  
pp. _20506-1_-_20506-2_
Author(s):  
Tadateru ISHIDE ◽  
Hiroki NAKAYAMA ◽  
Kazuya NAGANUMA ◽  
Keiju MAKIMOTO ◽  
Hiroyuki ISHIKAWA ◽  
...  
Keyword(s):  
Delta Wing ◽  
Leading Edge ◽  
Aerodynamic Characteristics

scholarly journals Experimental investigation of wing flexibility on force generation of a hovering flapping wing micro air vehicle with double wing clap-and-fling effects

2017 ◽  
Vol 9 (3) ◽  
pp. 187-197 ◽  
Author(s):  
Quoc V Nguyen ◽  
Woei L Chan ◽  
Marco Debiasi
Keyword(s):  
Experimental Investigation ◽  
Power Consumption ◽  
High Speed ◽  
Electrical Power ◽  
Leading Edge ◽  
Flapping Wing ◽  
Micro Air Vehicle ◽  
Custom Made ◽  
Air Vehicle ◽  
Set Up

Experimental investigation of wing flexibility on vertical thrust generation and power consumption in hovering condition for a hovering Flapping-Wing Micro Air Vehicle, namely FlowerFly, weighing 14.5 g with a 3 g onboard battery and having four wings with double wing clap-and-fling effects, was conducted for several wing configurations with the same shape, area, and weight. A data acquisition system was set up to simultaneously record aerodynamic forces, electrical power consumption, and wing motions at various flapping frequencies. The forces and power consumption were measured with a loadcell and a custom-made shunt circuit, respectively, and the wing motion was captured by high-speed cameras. The results show a phase delay of the wing tip displacement observed for wings with high flexible leading edge at high frequency, resulting in less vertical thrust produced when compared with the wings with less leading edge flexibility at the same flapping frequency. Positive wing camber was observed during wing flapping motion by arranging the wing supporting ribs. Comparison of thrust-to-power ratios between the wing configurations was undertaken to figure out a wing configuration for high vertical thrust production but less power consumption.

Impact of Gurney Flaplike Strips on the Aerodynamic and Vortex Flow Characteristic of a Reverse Delta Wing

2016 ◽  
Vol 138 (6) ◽  
Author(s):  
T. Lee
Keyword(s):  
Vortex Flow ◽  
Delta Wing ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Aerodynamic Characteristics ◽  
Force Balance ◽  
Vortex Control ◽  
Lift Curve ◽  
Lift And Drag ◽  
The Impact

The impact of Gurney flaplike strips, of different geometric configurations and heights, on the aerodynamic characteristics and the tip vortices generated by a reverse delta wing (RDW) was investigated via force-balance measurement and particle image velocimetry (PIV). The addition of side-edge strips (SESs) caused a leftward shift of the lift curve, resembling a conventional trailing-edge flap. The large lift increment overwhelmed the corresponding drag increase, thereby leading to an improved lift-to-drag ratio compared to the baseline wing. The lift and drag coefficients were also found to increase with the strip height. The SES-equipped wing also produced a strengthened vortex compared to its baseline wing counterpart. The leading-edge strips (LESs) were, however, found to persistently produce a greatly diffused vortex flow as well as a small-than-baseline-wing lift in the prestall α regime. The downward LES delivered a delayed stall and an increased maximum lift coefficient compared to the baseline wing. The LESs provide a potential wingtip vortex control alternative, while the SESs can enhance the aerodynamic performance of the RDW.

A Review of Bird-Inspired Flapping Wing Miniature Air Vehicle Designs

2010 ◽  
Author(s):  
John W. Gerdes ◽  
Satyandra K. Gupta ◽  
Stephen A. Wilkerson
Keyword(s):  
Aerodynamic Characteristics ◽  
Flapping Wing ◽  
Research Groups ◽  
Advantages And Disadvantages ◽  
Air Vehicle ◽  
Different Types ◽  
Comprehensive Listing ◽  
Test Flight ◽  
Distinguishing Features ◽  
Design Challenges

Physical and aerodynamic characteristics of the bird in flight may offer benefits over typical propeller or rotor driven miniature air vehicle (MAV) locomotion designs in certain types of scenarios. A number of research groups and companies have developed flapping wing vehicles that attempt to harness these benefits. The purpose of this paper is to report different types of flapping wing designs and compare their salient characteristics. For each category, advantages and disadvantages will be discussed. The discussion presented will be limited to miniature-sized flapping wing air vehicles, defined as 10–100 grams total weight. The discussion will be focused primarily on ornithopters which have performed at least one successful test flight. Additionally, this paper is intended to provide a representation of the field of current technology, rather than providing a comprehensive listing of all possible designs. This paper will familiarize a newcomer to the field with existing designs and their distinguishing features. By studying existing designs, future designers will be able to adopt features from other successful designs. This paper also summarizes the design challenges associated with the further advancement of the field and deploying flapping wing vehicles in practice.

Generic Theoretical and Experimental Development of Micro Aerial Vehicle Using Fundamental Principles

2014 ◽  
Vol 564 ◽  
pp. 110-117
Author(s):  
Harijono Djojodihardjo ◽  
Muljo Widodo Kartidjo
Keyword(s):  
Leading Edge ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Theoretical Development ◽  
Phase Lag ◽  
Test Bed ◽  
Experimental Development ◽  
New Variant ◽  
Air Vehicle ◽  
Air Vehicles

Flapping Wing Micro Air Vehicles (FWMAV) and Quad-Rotor Micro Air Vehicles (QRMAV) are strategic for many applications, applications, ranging from control device test bed to perform difficult tasks as well as to perform surveillance mission to unreachable places. While salient features and functional significance of the various components in the flying bio-systems can be synthesized into a simplified and generic and simplified model of a flapping Bi-Wing and Quad-Wing Ornithopter; Quad-Rotor Micro Air Vehicle could be utilized for developing emerging Personal Air Vehicle (PAV) technologies. Theoretical development of Bio-Inspired Bi-Wing and Quad-Wing Flapping Wing Micro Air Vehicles is outlined by considering the motion of a three-dimensional rigid and thin wing in flapping and pitching motion with phase lag. Basic Unsteady Aerodynamic Approach incorporating viscous effect and leading-edge suction is utilized. Theoretical and experimental development of a new variant of Quad-Rotor Micro Air Vehicles is also outlined. The theoretical development of these potential MAVs is carried out using a first principle approach starting from the Euler-Newton equations of motion.

Flow Regimes over Delta Wings at Supersonic and Hypersonic Speeds

1976 ◽  
Vol 27 (1) ◽  
pp. 1-14 ◽  
Author(s):  
L C Squire
Keyword(s):  
Shock Layer ◽  
Delta Wing ◽  
Leading Edge ◽  
Flow Regimes ◽  
Lower Surface ◽  
Delta Wings ◽  
Thin Shock Layer ◽  
Wide Range ◽  
Wing Sweep ◽  
Edge Separation

SummaryThis paper concerns the boundaries between flow regimes for sharp-edged delta wings in supersonic flow and the relation of some predictions of thin-shock-layer theory to these boundaries. In particular, it is shown that the theory predicts that the attachment lines on the lower surface of a thin delta wing at supersonic speeds suddenly jump from just inboard of the leading edges to the centre line in certain flight conditions. In general there is close agreement between the conditions for this jump and the flight conditions corresponding to the change-over from attached flow to the leading-edge separation on the upper surface. Since the movement of the attachment lines on the lower surface must change the position of the sonic line and the nature of the expansion around the edge, it is suggested that the two phenomena are directly related. Thus thin-shock-layer theory can be used to establish the boundaries of the various flow regimes for a wide range of Mach number, incidence and wing sweep. The theory can also be used to predict the effects of wing thickness on leading-edge separation, but here the experimental data is very sparse and somewhat contradictory, so the value of the prediction in the case of thickness requires further investigation.

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