Abstract
Micro air vehicles are gaining attention due to their wide range of applications in civilian and defense fields. The wings of these vehicles generate a particular flow regime which is to be explored further. Since the theories on the aerodynamics of all affects are still to be investigated, simulation based computational fluid dynamics is a good approach rather than wind tunnel experiments which involves cost and long periods of experimentation. This study mainly emphasize on the lift, lift coefficient, drag and drag coefficient with respect to Reynold’s number and angle of attack, by modelling and analyzing the fixed wing of a micro air vehicle. The analysis has been done selecting NACA25411 air foil. Modelling has been done in Gambit and analysis is taken up using Fluent. Angle of attack and Reynold’s number have been optimized to increase the lift and decrease the drag.
Highlights
Over the past decade, Micro Air Vehicles (MAVs) have received an increasing amount of attention due to their unique capabilities in missions as covert imaging, biological and chemical agent detection, battlefield surveillance, traffic monitoring and urban intelligence gathering
The lift, lift coefficients, drag and drag coefficients obtained by varying Reynolds number (ReNo) at a constant angle of attack are given in Table 2 to 6
The influence of angle of attack on drag and drag coefficients for the ReNos considered for the present investigation as presented in Fig. 5 and 6
Summary
Micro Air Vehicles (MAVs) have received an increasing amount of attention due to their unique capabilities in missions as covert imaging, biological and chemical agent detection, battlefield surveillance, traffic monitoring and urban intelligence gathering. MAVs generally fly in the Reynolds number (ReNo) range of 1000 to 120000. Mueller (1999) has conducted extensive experimental studies on 2D and 3D flow around flat plates and cambered airfoils at ReNos ranging from 60000 to 200000.
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