Comparative study on analytical and computational aerodynamic models for flapping wings MAVs

2020 ◽  
Vol 124 (1280) ◽  
pp. 1636-1665
Author(s):  
M.F. Valdez ◽  
B. Balachandran ◽  
S. Preidikman
Keyword(s):  
Cfd Simulation ◽  
Time History ◽  
Leading Edge ◽  
Micro Air Vehicles ◽  
Detailed Comparison ◽  
Flapping Wings ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Analytical Potential ◽  
History Of

ABSTRACTA range of quasi-steady and unsteady aerodynamic models are used to predict the aerodynamic forces experienced by a flapping wing and a detailed comparison amongst these predictions in provided. The complexity of the models ranges from the analytical potential flow model to the computational Unsteady Vortex Lattice Method (UVLM), which allows one to describe the motion of the wake and account for its influence on the fluid loads. The novelty of this effort lies in a modification of the predicted forces as a generalisation of the leading edge suction analogy. This modification is introduced to account for the delayed stall mechanism due to leading edge flow separation. The model predictions are compared with two sets of independent experimental data and with computational fluid dynamics (CFD) simulation data available in the literature. It is found that both, the modified analytical model and the UVLM model can be used to describe the time history of the lift force, in some cases with better results than a high-fidelity CFD model. The models presented here constitute a useful basis for the aerodynamic design of bioinspired flapping-wings micro-air vehicles.

Modified Unsteady Vortex-Lattice Method to Study Flapping Wings in Hover Flight

AIAA Journal ◽  
2013 ◽  
Vol 51 (11) ◽  
pp. 2628-2642 ◽  
Author(s):  
Bruno A. Roccia ◽  
Sergio Preidikman ◽  
Julio C. Massa ◽  
Dean T. Mook
Keyword(s):  
Vortex Lattice ◽  
Flapping Wings ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Hover Flight

scholarly journals Unsteady Aerodynamics of Highly Maneuvering Flyers

2021 ◽  
Author(s):  
Mohamed Yehia Zakaria
Keyword(s):  
Unsteady Aerodynamics ◽  
Leading Edge ◽  
High Amplitude ◽  
Analytical Models ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Classical Models ◽  
Zero Degree ◽  
Edge Vortex ◽  
Unsteady Lift

In this chapter, a set of analytical aerodynamic models, based on potential flow, that can be used to predict the unsteady lift response during pitching maneuvers are presented and assessed. The result examines the unsteady lift coefficients experienced by a flat plate in high-amplitude pitch ramp motion. The pitch ramps are chosen based on two ramp pitch maneuvers of a maximum amplitudes of 25 and 45 degrees starting from zero degree. The aim is investigate the use of such classical models in predicting the lift dynamics compared to a full physical-based model. Among all classical methods used, the unsteady vortex lattice method (without considering the leading edge vortex) is found to be a very good predictor of the motion lift dynamic response for the 25° ramp angle case. However, at high pitch maneuvers (i.e.,the 45° ramp angle case), could preserve the response pattern with attenuated amplitudes without high computational burden. These mathematical analytical models presented in this chapter can be used to obtain a fast estimate for aircraft unsteady lift during pitch maneuvers instead of high fidelity models, especially in the early design phases.

3D Simulation of a Convergent-Divergent Aero Engine Intake, Using Two Different CFD Methods

2005 ◽  
Author(s):  
Ioannis Templalexis ◽  
Pericles Pilidis ◽  
Geoffrey Guindeuil ◽  
Theodoros Lekas ◽  
Vassilios Pachidis
Keyword(s):  
Vortex Lattice ◽  
Cfd Simulation ◽  
Three Dimensional ◽  
Internal Flow ◽  
Navier Stokes ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Aero Engine ◽  
Flow Effects ◽  
Development And Validation

This study refers to the development and validation of a Three Dimensional (3D) Vortex Lattice Method (VLM) to be used for internal flow case studies and more precisely aero-engine intake simulation. It examines the quantitative and qualitative response of the method to a convergent – divergent intake, produced as a surface of revolution of the CFM56-5B2 upper lip geometry. The study was carried out for three different sections namely: Intake outlet, intake throat and intake inlet. Moreover five different settings of Angle Of Attack (AOA) were considered. The VLM was based on an existing code. It was modified to accommodate internal flow effects and match, as closely as possible, the boundary conditions set by the Reynolds Average Navier-Stokes (RANS) Computational Fluid Dynamics (CFD) simulation. In the context of this study, Vortex Lattice-derived average values velocity profiles were compared against RANS CFD results.

Flapping wings in line formation flight: a computational analysis

2014 ◽  
Vol 118 (1203) ◽  
pp. 485-501 ◽  
Author(s):  
M. Ghommem ◽  
V. M. Calo
Keyword(s):  
Power Consumption ◽  
Aerodynamic Performance ◽  
Formation Flight ◽  
Flapping Wings ◽  
Line Formation ◽  
Lattice Method ◽  
Flow Solver ◽  
Vortex Lattice Method ◽  
Bird Evolution ◽  
Unsteady Effects

AbstractThe current understanding of the aerodynamics of birds in formation flights is mostly based on field observations. The interpretation of these observations is usually made using simplified aerodynamic models. Here, we investigate the aerodynamic aspects of formation flights. We use a potential flow solver based on the unsteady vortex lattice method (UVLM) to simulate the flow over flapping wings flying in grouping arrangements and in proximity of each other. UVLM has the capability to capture unsteady effects associated with the wake. We demonstrate the importance of properly capturing these effects to assess aerodynamic performance of flapping wings in formation flight. Simulations show that flying in line formation at adequate spacing enables significant increase in the lift and thrust and reduces power consumption. This is mainly due to the interaction between the trailing birds and the previously-shed wake vorticity from the leading bird. Moreover, enlarging the group of birds flying in formation further improves the aerodynamic performance for each bird in the flock. Therefore, birds get significant benefit of such organised patterns to minimise power consumption while traveling over long distances without stop and feeding. This justifies formation flight as being beneficial for bird evolution without regard to potential social benefits, such as, visual and communication factors for group protection and predator evasion.

scholarly journals An Integrated Program to Simulate the Multibody Dynamics of Flapping Flight  

2020 ◽  
Vol 31 (1) ◽  
pp. 76-84
Keyword(s):  
Multibody Dynamics ◽  
Vortex Lattice ◽  
Lagrange Equation ◽  
Micro Air Vehicles ◽  
Flapping Flight ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Runge Kutta Method ◽  
Air Vehicle ◽  
Integrated Program

This paper presents an in-house developed program that couples multibody dynamics and aerodynamics codes to simulate flapping flight of insects and micro air vehicles. The multibody dynamics code is built based on the numerical solution of the Lagrange equation, while the extended unsteady vortex-lattice method is employed to develop the aerodynamics code. The solution from the governing equation is obtained by the use of the fourth-order Runge-Kutta method and validated against the simulation results from a commercial software MSC Adams for a micro air vehicle model. In this work, parallel computing techniques are applied while estimating the aerodynamics force to minimize the running time of the program.

Extended Unsteady Vortex-Lattice Method for Insect Flapping Wings

2016 ◽  
Vol 53 (6) ◽  
pp. 1709-1718 ◽  
Author(s):  
Anh Tuan Nguyen ◽  
Joong-Kwan Kim ◽  
Jong-Seob Han ◽  
Jae-Hung Han
Keyword(s):  
Vortex Lattice ◽  
Flapping Wings ◽  
Lattice Method ◽  
Vortex Lattice Method

Modified Unsteady Vortex Lattice Method for Aerodynamics of Flapping Wing Models

2015 ◽  
Author(s):  
Anh Tuan Nguyen ◽  
Jae-Hung Han
Keyword(s):  
Vortex Lattice ◽  
Micro Air Vehicles ◽  
Flapping Wing ◽  
Preliminary Design ◽  
Aerodynamic Forces ◽  
Lattice Method ◽  
Real Motion ◽  
Flapping Motion ◽  
The Real ◽  
Vortex Lattice Method

Motivated by extensive possible applications of flapping-wing micro-air vehicles (MAVs) to various different areas, there has been an increasing amount of research related to this issue. In the stage of preliminary studies, one of the most important tasks is to predict the aerodynamic forces generated by the flapping motion. Studying aerodynamics of insects is an efficient way to approach the preliminary design of flapping-wing MAVs. In this paper, a modified version of an Unsteady Vortex Lattice Method (UVLM) is developed to compute aerodynamic forces appearing in flapping-wing models. A hawkmoth-like wing with kinematics based on the real motion is used for the simulations in this paper.

Generalized vortex lattice method for planar supersonic flow

AIAA Journal ◽  
1997 ◽  
Vol 35 ◽  
pp. 1230-1233
Author(s):  
Paulo A. O. Soviero ◽  
Hugo B. Resende
Keyword(s):  
Supersonic Flow ◽  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice Method

PROGRAM OF PREDICTION AND MANAGEMENT OF COINTEGED DYNAMIC ECONOMIC PROCESSES BASED ON THE CYBERNETIC APPROACH

2019 ◽  
Author(s):  
Olena Bundak ◽  
Nataliia Zubovetska
Keyword(s):  
Computer Program ◽  
Pair Correlation ◽  
Time History ◽  
Critical Area ◽  
Concrete Object ◽  
Graphic Arts ◽  
Ex Post ◽  
History Of ◽  
Successive Change ◽  
Rms Errors

A method and computer program ConRow, which prognostication of development of the dynamically CPLD economic transients is executed by, is described in the article. Such prognostication of economic processes is very important in the cases when their development can result in undesirable consequences, that to go out in the so-called critical area. Extrapolation in a critical area with the use of information about the conduct of the system at an area, near to it, allows to estimate to the lead through of experiment in the critical area of his consequence. For the imitation of conduct of object the function of review is set on entrance influence. For a concrete object this function can express, for example, dependence of change of level sale from time-history of charges on advertising and set as a numeral row. Statistics as a result of analysis of row are represented in a table, where the level of meaningfulness is set statistician, and also parameters of the handed over criteria. The graphic reflection of information is intended for visualization of analysis. Here represented on the points of graphic arts, the crooked smoothing which are calculated as полиномиальные regressions is added. The best approaching is controlled by sight on the proper graph, and also by minimization of their rms errors. Models of prognostication by sight and as formulas represented on graphic arts, the middle is here determined tailings and their chance is checked up on statistics of signs. After the got models determined also and prognosis values of influences and reviews. Establishing an order models of Сr(p) of co integrate regression is carried out separate custom controls. The coefficient of clay correlation of ruФ shows by itself pair correlation between lines with a successive change in relation to each other on a size to лагу of l = 1, 2, 3 . The program was tested on the example of ex-post prognosis at establishing an integration connection and possibility of prognostication of growth of nominal average monthly settlings on the basis of these statistical indexes of consumer inflation in Ukraine.

Bio-Mimetic Millimeter-Scale Flapping Wings for Micro Air Vehicles

2009 ◽  
Author(s):  
Christopher Kroninger ◽  
Jeffrey Pulskamp ◽  
Jessica Bronson ◽  
Ronald G. Polcawich ◽  
Eric Wetzel
Keyword(s):  
Micro Air Vehicles ◽  
Flapping Wings ◽  
Air Vehicles
Sign in / Sign up

Export Citation Format

Share Document