CFD Simulation of Flow Past MAV Wings

Pradeep, Shetty; Subrahmanya, MB; Kulkarni, DS; Rajani, BN

doi:10.1260/1757-2258.5.1.19

Cited by 4 publications

(2 citation statements)

References 19 publications

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“…The aerodynamics at this range of Reynolds number is one of the most interesting and less understood aspects. 5 Based upon lift and thrust forces generation, we can classify the MAVs into fixed wings, rotary wings, and flapping wings. 6 In nature, the greatest optimizer, there are no examples of fixed wings or even rotary wings.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic study of the corrugated airfoil at ultra-low Reynolds number

El-Latief

Elsayed

Abdelrahman

2019

Advances in Mechanical Engineering

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In this study, Aeshna cyanea dragonfly forewing mid-cross-section corrugated airfoil was simulated at ultra-low Reynolds number. The corrugated airfoil was compared with its smooth counterpart to study the effect of the corrugations upon the aerodynamic performance. Unsteady two-dimensional laminar flow was solved using FLUENT. This study was divided into gliding phase and flapping phase. In the gliding phase, the corrugated airfoil produced a higher lift force with respect to the profiled airfoil at both tested Reynolds numbers ([Formula: see text], [Formula: see text]) with comparable drag coefficient for all the tested angles of attack. In the flapping phase, both the corrugated airfoil and the flat-plate have a very similar flow behavior which yields a very similar aerodynamic performance at Re[Formula: see text]. A structural analysis was performed to compare the corrugated airfoil with the flat-plate. The analysis revealed the superiority of the corrugated airfoil over the flat-plate in decreasing the deflection under the applied load. The reduced frequency was varied to study its impact on the aerodynamic performance. By increasing the reduced frequency, the thrust and the lift forces increased by [Formula: see text]% and [Formula: see text]%, respectively. Any increase in the reduced frequency will increase lift and thrust forces, but the propulsive efficiency will deteriorate.

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Section: Introductionmentioning

confidence: 99%

Aerodynamic study of the corrugated airfoil at ultra-low Reynolds number

El-Latief

Elsayed

Abdelrahman

2019

Advances in Mechanical Engineering

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“…Penelitian ini melakukan analisis performa aerodinamika suatu penampang airfoil untuk menentukan gaya angkat maksimum yang terjadi serta gaya-gaya yang bekerja pada penampang airfoil seperti gaya drag dan gaya lift. (Shetty et al, 2013) melakukan penelitian dengan judul "Simulasi CFD Arus/ Aliran yang Melewati MAV Sayap". Penelitian ini melakukan analisis Simulasi aliran turbulen melewati sayap tipis rasio aspek rendah (AR) yang digunakan untuk Konfigurasi MAV (Micro Air Vehicle) untuk menganalisis karakteristik aerodinamisnya.…”

Section: Pendahuluanunclassified

Analisis CFD Pada Sayap Mini Glider Dengan Penampang Low Reynold Number Airfoil Dan Folded Flat Plate Airfoil

Dede Dahendi,

Yudhono,

Armelia Erissonia

2023

teknika

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The purpose of this research is to make a very small unmanned aircraft as a teaching aid in aerospace engineering workshops, because of its very small size, this type of unmanned aircraft is abbreviated as Micro Air Vehicle, this MAV is only operated at low Reynolds numbers. MAV development research for smaller sizes continues to be carried out such as the Micro Glider. In this study, the author uses the Computational Fluid Dynamic method and the software used ANSYS Fluent and compares the existing DATCOM data, the author simulates the 4 types of airfoils into a wing object. The results of this study can be seen that based on the average deviation diff value that has been obtained in a population to determine the error from the comparison of the reference airfoil lift coefficient and its FFP by comparing the two methods, namely the IISHI airfoil reference geometry is 6.22% while the FFP is is 11.25% and the SD 7037 airfoil reference geometry is 3.71% while the FFP is 2.11%. Then for the comparison of the maximum lift to drag ratio values, it is obtained that the airfoil reference geometry (SD 7037) has a value of = 9.96 while the airfoil reference geometry (IISHI) has a value of = 8.81. In the Folded Flat Plate airfoil geometry (SD 7037) it has a value of = 7.61 while the Folded Flat Plate airfoil (IISHI) has a value of = 7.37. Then for the visualization of fluid flow can be obtained, namely the results of visualization of fluid flow in several parts of the angle of view / plane of the wing geometry when the AoA is high, namely the root plane to the half wing plane. early, while the geometry of SD 7037 (airfoil reference) is not easy to occur early turbulence flow. Second, that in general the fluid flow pattern seen in the FFP airfoil geometry (FFP IISHI) has the most dominant turbulence flow pattern (very much/large) while the FFP airfoil geometry (FFP SD 7037) has very little/small turbulence flow pattern..

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Transition Prediction for Flow Over a MAV Wing Using the Correlation Based Model

Subrahmanya¹,

Rajani²

2021

Lecture Notes in Mechanical Engineering

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CFD Simulation of Flow Past MAV Wings

Cited by 4 publications

References 19 publications

Aerodynamic study of the corrugated airfoil at ultra-low Reynolds number

Aerodynamic study of the corrugated airfoil at ultra-low Reynolds number

Analisis CFD Pada Sayap Mini Glider Dengan Penampang Low Reynold Number Airfoil Dan Folded Flat Plate Airfoil

Transition Prediction for Flow Over a MAV Wing Using the Correlation Based Model

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