Experimental investigation of propeller slipstream effects on the wing aerodynamics and boundary layer treatment at low Reynolds number

Aminaei, Hamzeh; Manshadi, Mojtaba Dehghan; Mostofizadeh, A R

doi:10.1177/0954410018793703

Cited by 7 publications

(5 citation statements)

References 11 publications

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“…This depicts a small amount of roll that causes yaw and yaw causes roll phenomenon in fixed wing micro aerial vehicles. It is highlighted that propeller effects on low aspect ratio wings have been studied earlier through wind tunnel experimentation by various researchers [46][47][48][49]. However, for correct six degree of freedom modeling applications, it is recommended that dependency of aerodynamic coefficients on advance ratios rather than propeller rotation may also be studied.…”

Section: Implementation Of a 6-dof Modelmentioning

confidence: 99%

Airfoil Selection Procedure, Wind Tunnel Experimentation and Implementation of 6DOF Modeling on a Flying Wing Micro Aerial Vehicle

et al. 2020

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Airfoil selection procedure, wind tunnel testing and an implementation of 6-DOF model on flying wing micro aerial vehicle (FWMAV) has been proposed in this research. The selection procedure of airfoil has been developed by considering parameters related to aerodynamic efficiency and flight stability. Airfoil aerodynamic parameters have been calculated using a potential flow solver for ten candidate airfoils. Eppler-387 proved to be the most efficient reflexed airfoil and therefore was selected for fabrication and further flight testing of vehicle. Elevon control surfaces have been designed and evaluated for longitudinal and lateral control. The vehicle was fabricated using hot wire machine with EPP styrofoam of density 50 Kg/ m 3 . Static aerodynamic coefficients were evaluated using wind tunnel tests conducted at cruise velocity of 20 m/s for varying angles of attack. Rate derivatives and elevon control derivatives have also been calculated. Equations of motion for FWMAV have been written in a body axis system yielding a 6-DOF model. It was found during flight tests that vehicle conducted coordinated turns with no appreciable adverse yaw. Since FWMAV was not designed with a vertical stabilizer and rudder control surface, directional stability was therefore augmented through winglets and high wing leading edge sweep. Major problems encountered during flight tests were related to left rolling tendency. The left roll tendency was found inherent to clockwise rotating propeller as ‘P’ factor, gyroscopic precession, torque effect and spiraling slipstream. To achieve successful flights, many actions were required including removal of excessive play from elevon control rods, active actuation of control surfaces, enhanced launch speed during take off, and increased throttle control during initial phase of flight. FWMAV flew many successful stable flights in which intended mission profile was accomplished, thereby validating the proposed airfoil selection procedure, modeling technique and proposed design.

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Section: Implementation Of a 6-dof Modelmentioning

confidence: 99%

Airfoil Selection Procedure, Wind Tunnel Experimentation and Implementation of 6DOF Modeling on a Flying Wing Micro Aerial Vehicle

et al. 2020

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“…Due to the low moment of inertia of the fixed wing MAV, motor counter-torque contributes to a significant part of rolling moment acting on MAV. In equations (9) and (10), expression of rolling moment (l) is given…”

Section: Rolling Momentmentioning

confidence: 99%

“…In this region, the lift to drag (LD) ratio reduces drastically due to the formation of a laminar separation bubble. 8 The size of the propeller dimension to the wing dimension is comparable in the case of propeller-driven MAV; hence, the effect of the propeller-induced flow on the overall aerodynamics is quite significant as it influences the flow transition, 9 flow separation, flow reattachment and formation of laminar separation bubbles. 10 The important parameters that are affected by the propulsive forces are stall angle of attack (AoA), 11 lift coefficient ( C L ), and drag coefficient (CD), 12 the slope of lift versus AoA curve, 13 LD ratio, 14,15 pitching moment, 16 etc.…”

Section: Introductionmentioning

confidence: 99%

Effect of propeller-induced flow on the performance of biplane micro air vehicle dynamics

Jana

Kandath

Shewale

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper presents the analysis of propeller-induced flow effects on the dynamics of a fixed wing biplane micro air vehicle. The analysis is based on wind tunnel tests and mathematical modeling. This analysis plays a pivotal role because the propeller-induced flow has significant effects on the dynamics of fixed wing micro air vehicle due to submergence of a large portion of the wing in propeller slipstream. Although the effect of the propeller-induced flow on the various aerodynamic parameter is reported in the literature; however, its effects on overall forces, moments and vehicle dynamics are not quantified so far. In this paper, propeller-induced flow effects are modeled as a function of motor rotation speed and mathematical analysis is performed to quantify their effects. The wind tunnel test is conducted at different propeller speeds on a biplane micro air vehicle “Skylark”, having wingspan and chord length of 150 mm and 140 mm, respectively. Analysis of results shows that the propeller slipstream increases the overall lift, drag, side force, range, and endurance significantly. Propeller flow also contributes to the rolling moment and the pitching moment, while it has negligible effects on the yawing moment. It is shown that the trim angle of attack is lower when the propeller flow is considered in computing the trim conditions.

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“…These tests are carried out in a wind tunnel using measuring systems that measure forces and pressure distribution. Pressure taps combined with pressure sensors [ 13 ] or the PIV (Particle Image Velocimetry) method [ 14 , 15 ] can be used to measure pressure distribution. The issue of testing the small propeller and the rotor in a low-speed aeroacoustic wind tunnel is discussed in [ 16 , 17 ].…”

Section: Introductionmentioning

confidence: 99%

Wind Tunnel Performance Tests of the Propellers with Different Pitch for the Electric Propulsion System

Czyż

Karpiński

Skiba

et al. 2021

Sensors

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The geometry of a propeller is closely related to its aerodynamic performance. One of the geometric parameters of a propeller is pitch. This parameter determines the distance by which the propeller moves forward during one revolution. The challenge is to select a propeller geometry for electric propulsion in order to achieve the best possible performance. This paper presents the experimental results of the aerodynamic performance of the set of propellers with different pitch values. The tests were performed in a closed-circuit subsonic wind tunnel using a six-component force balance. The analyzed propellers were 12-inch diameter twin-blade propellers that were driven by a BLDC (brushless direct current) electric motor. The tests were performed under forced airflow conditions. The thrust and torque produced by the propeller were measured using a strain gauge. The analysis was performed for different values of the advance ratio which is the ratio of freestream fluid speed to propeller tip speed. Additionally, a set of electrical parameters was recorded using the created measurement system. The propeller performance was evaluated by a dimensional analysis. This method enables calculation of dimensionless coefficients which are useful for comparing performance data for propellers.

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Experimental investigation of propeller slipstream effects on the wing aerodynamics and boundary layer treatment at low Reynolds number

Cited by 7 publications

References 11 publications

Airfoil Selection Procedure, Wind Tunnel Experimentation and Implementation of 6DOF Modeling on a Flying Wing Micro Aerial Vehicle

Airfoil Selection Procedure, Wind Tunnel Experimentation and Implementation of 6DOF Modeling on a Flying Wing Micro Aerial Vehicle

Effect of propeller-induced flow on the performance of biplane micro air vehicle dynamics

Wind Tunnel Performance Tests of the Propellers with Different Pitch for the Electric Propulsion System

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