Experimental Analysis of Propeller-Wing Interactions for a Micro Air Vehicle

Gamble, Brian J.; Reeder, Mark F.

doi:10.2514/1.34520

Cited by 25 publications

(19 citation statements)

References 13 publications

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“…Increased axial velocity along with swirl velocity can enhance wings aerodynamic efficiency. However, Sergey [29] found, that maximum figure of merit could be obtained in pusher configuration which Gamble negated [32]. FOM is usually defined for helicopter rotor during hover phase.…”

Section: Effects Of Propeller Helical System On Aircraft Aerodynmentioning

confidence: 99%

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

et al. 2020

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In this research effect of propeller induced flow on aerodynamic characteristics of low aspect ratio flying wing micro aerial vehicle has been investigated experimentally in subsonic wind tunnel. Left turning tendencies of right-handed propellers have been discussed in literature, but not much work has been done to quantify them. In this research, we have quantified these tendencies as a change in aerodynamic coefficient with a change in advance ratio at a longitudinal trim angle of attack using subsonic wind tunnel. For experimental testing, three fixed pitch propeller diameters (5 inch, 6 inch and 7 inch), three propeller rotational speeds (7800, 10800 and 12300 RPMs) and three wind tunnel speeds (10, 15 and 20 m/s) have been considered to form up 27 advance ratios. Additionally, wind tunnel tests of 9 wind mill cases were conducted and considered as baseline. Experimental uncertainty assessment for measurement of forces and moments was carried out before conduct of wind tunnel tests. Large variation in lift, drag, yawing moment and rolling moment was captured at low advance ratios, which indicated their significance at high propeller rotational speeds and large propeller diameters. Side force and pitching moment did not reflect any significant change. L D at trim point was found a nonlinear function of propeller diameter to wingspan ratio D b , and propeller rotational speed. Rate and control derivatives were obtained using unsteady vortex lattice method with propeller induced flow effect modeled by Helical Vortex Modeling approach. In this research, we have proposed improved 6-DOF equations of motion, with a contribution of advance ratio J. It is concluded, that propeller induced flow effects have a significant contribution in flight dynamic modeling for vehicles with large propeller diameter to wingspan ratio, D b of 22% or more. INDEX TERMS Advance ratio, aerodynamic characteristics, flying wing micro aerial vehicle, Propeller induced flow, , wind tunnel testing, 6DOF Modeling

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Section: Effects Of Propeller Helical System On Aircraft Aerodynmentioning

confidence: 99%

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

et al. 2020

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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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“…However, accurate prediction of the complex flow field of a low-aspect-ratio wing with propeller slipstream using computational methods is still challenging, especially at low Reynolds number for high angle of incidence. Gamble and Reeder (20) carried out force and velocity field measurements on rigid and flexible wing MAVs under propeller-on conditions at a distance of one propeller diameter. They found that the propeller slipstream increases the streamwise velocity by a factor of 1.16.…”

Section: Introductionmentioning

confidence: 99%

Influence of propeller slipstream on vortex flow field over a typical micro air vehicle

2016

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An experimental study has been carried out to explore the effect of propeller-induced slipstream on the vortex flow field on a fixed-wing Micro Air Vehicle (MAV). Experiments were conducted at a freestream velocity of 10 m/s, corresponding to a Reynolds number based on a root chord of about 1.6 × 105. Surface flow topology on the surface of the MAV wing at propeller-off and propeller-on conditions was captured using surface oil flow visualisation at four angles of incidence. The mean off-body flow over the MAV was documented in the four spanwise planes at different chord position using Stereoscopic Particle Image Velocimetry (SPIV) technique at angle-of-attack of 24° for both conditions. The oil flow visualisation showed minimal differences in flow patterns for propeller-off and propeller-on conditions at 10° and 15° incidence. The small asymmetry between port and starboard side observed at 20° during the propeller-off condition became significantly pronounced at 24°. The fuselage stub which is necessary for housing the motor of the propeller was seen to have a significant effect on the flow symmetry at large incidences that can occur when the MAV encounters sudden vertical gusts. Switching on the propeller restored the symmetry at both incidences. SPIV measurements were carried out at the incidence of 24° which exhibited the highest asymmetry. The off-body data shows the re-establishment of symmetry during propeller-on condition owing to the increase in the magnitude of spanwise and vertical velocities as a result of the propeller slipstream. The findings emphasise the importance of considering the propeller flow and design of the motor housing while evaluating the aerodynamics of low-aspect-ratio MAVs.

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Experimental Analysis of Propeller-Wing Interactions for a Micro Air Vehicle

Cited by 25 publications

References 13 publications

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

Experimental Investigation of Propeller Induced Flow on Flying Wing Micro Aerial Vehicle for Improved 6DOF Modeling

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

Influence of propeller slipstream on vortex flow field over a typical micro air vehicle

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