Numerical study on the flow characteristics of micro air vehicle wings at low Reynolds numbers

Xiao, Tianhang; Li, Zhengzhou; Deng, Shuanghou; Ang, Haisong; Xin-chun, Zhou

doi:10.1177/1756829316638204

Cited by 4 publications

(2 citation statements)

References 26 publications

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“…The results showed that the thin cambered-plate airfoil generated the highest lifting force compared with the NACA0012. Xiao [ 15 ] studied the aerodynamic performance of Eppler61, Pfenninger048, a thin cambered-plate airfoil and a flat-plate airfoil. The results showed that the thin cambered-plate airfoil provided the highest lift and lift-to-drag (L/D) ratio.…”

Section: Introductionmentioning

confidence: 99%

In-Hover Aerodynamic Analysis of a Small Rotor with a Thin Circular-Arc Airfoil and a Convex Structure at Low Reynolds Number

Lei

Wang

et al. 2023

Micromachines

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This study focused on the in-hover aerodynamics of a small rotor with a thin circular-arc airfoil and a convex structure at a low Reynolds number. The method combined computational fluid dynamics (CFD) with the blade element momentum theory (BEMT). The former was used for studying the two-dimensional parametric aerodynamics of the airfoil at a low Reynolds number and the latter was used for the prediction of the rotor’s hover performance. A novel thin circular-arc airfoil with a convex structure with a high aerodynamic performance, high structural strength, light weight and easy manufacturing process is presented in this paper. A convex curve on the upper surface was adopted to increase the thickness of the airfoil at partial chord, and a stiffener in the airfoil was installed to improve the structural strength of rotor span-wise. The aerodynamic performance of the airfoil was numerically simulated by the two-dimensional steady and incompressible Navier–Stokes equations. The in-hover performance of the rotor for small-scale vehicles was predicted by an improved version of the blade element momentum theory (BEMT). Finally, a carbon-fiber rotor with the presented airfoil was manufactured that had a diameter of 40 cm and a pitch of 6.2 inches. The analysis results were verified by experiments. It was shown that the maximum calculation errors were below 6%. The improved BEMT can be used in the analysis of in-hover micro-rotor aerodynamics at low Reynolds numbers.

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Section: Introductionmentioning

confidence: 99%

In-Hover Aerodynamic Analysis of a Small Rotor with a Thin Circular-Arc Airfoil and a Convex Structure at Low Reynolds Number

Lei

Wang

et al. 2023

Micromachines

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“…Hence, a conventional aircraft modeling techniques that do not take into account of propeller wake are inadequate to model the aerodynamic forces acting on MAV. The aerodynamic effects of propeller flow on MAV and small UAV are studied in [ 7 , 8 , 9 , 10 , 11 , 12 , 13 , 14 ]. The influence of propeller wake on the lift, drag and wing stall characteristics is reported in [ 7 , 8 , 9 , 10 , 11 , 12 , 13 , 14 ].…”

Section: Introductionmentioning

confidence: 99%

Modeling and Closed Loop Flight Testing of a Fixed Wing Micro Air Vehicle

et al. 2018

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This paper presents the nonlinear six degrees of freedom dynamic modeling of a fixed wing micro air vehicle. The static derivatives of the micro air vehicle are obtained through the wind tunnel testing. The propeller effects on the lift, drag, pitching moment and side force are quantified through wind tunnel testing. The dynamic derivatives are obtained through empirical relations available in the literature. The trim conditions are computed for a straight and constant altitude flight condition. The linearized longitudinal and lateral state space models are obtained about trim conditions. The variations in short period mode, phugoid mode, Dutch roll mode, roll subsidence mode and spiral mode with respect to different trim operating conditions is presented. A stabilizing static output feedback controller is designed using the obtained model. Successful closed loop flight trials are conducted with the static output feedback controller.

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Gust Response Analysis Using the Kriging Method for Laminar Flow

Sotoudeh

Barnes

2023

AIAA Journal

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This paper presents an input–output reduced-order aerodynamic model employing the kriging interpolation for laminar flow. The kriging interpolation is a regression method, particularly useful for large motions. In the targeted flow regime, the response includes unsteady vortex shedding at high angles of attack. The reduced-order model (ROM) predicts the aerodynamic response of a rigid airfoil to a ([Formula: see text]) gust under a wide range of angles of attack, gust lengths, and gust intensities. We study two algorithms for sampling training simulations, equally spaced and Latin hypercube methods. Both methods result in a ROM with an accurate prediction of aerodynamic forces and moments, given sufficient training points, particularly along the gust length axis. We use this ROM in coupling with the structural dynamics equations to study the aeroelastic response of a one-degree-of-freedom elastic airfoil. The aeroelastic gust response predictions are accurate for moderately large pitch angle deformation, using only the ROM created from computational fluid dynamics simulation of the rigid airfoil.

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Numerical study on the flow characteristics of micro air vehicle wings at low Reynolds numbers

Cited by 4 publications

References 26 publications

In-Hover Aerodynamic Analysis of a Small Rotor with a Thin Circular-Arc Airfoil and a Convex Structure at Low Reynolds Number

In-Hover Aerodynamic Analysis of a Small Rotor with a Thin Circular-Arc Airfoil and a Convex Structure at Low Reynolds Number

Modeling and Closed Loop Flight Testing of a Fixed Wing Micro Air Vehicle

Gust Response Analysis Using the Kriging Method for Laminar Flow

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