A Propeller Thrust and Torque Dynamometer for Wind Tunnel Models

Strain ◽  
2002 ◽  
Vol 38 (1) ◽  
pp. 3-10 ◽  
Author(s):  
A. F. Molland ◽  
S. R. Turnock
Keyword(s):  
Wind Tunnel ◽  
Thrust And Torque ◽  
Propeller Thrust

Development and Validation of a CFD Technique for the Aerodynamic Analysis of HAWT

2009 ◽  
Vol 131 (3) ◽  
Author(s):  
S. Gómez-Iradi ◽  
R. Steijl ◽  
G. N. Barakos
Keyword(s):  
Wind Tunnel ◽  
Wind Turbine ◽  
Wind Turbines ◽  
Turbine Blades ◽  
Wind Tunnel Test ◽  
Unsteady Aerodynamics ◽  
Tunnel Wall ◽  
Local Flow ◽  
Flow Angle ◽  
Thrust And Torque

This paper demonstrates the potential of a compressible Navier–Stokes CFD method for the analysis of horizontal axis wind turbines. The method was first validated against experimental data of the NREL/NASA-Ames Phase VI (Hand, et al., 2001, “Unsteady Aerodynamics Experiment Phase, VI: Wind Tunnel Test Configurations and Available Data Campaigns,” NREL, Technical Report No. TP-500-29955) wind-tunnel campaign at 7 m/s, 10 m/s, and 20 m/s freestreams for a nonyawed isolated rotor. Comparisons are shown for the surface pressure distributions at several stations along the blades as well as for the integrated thrust and torque values. In addition, a comparison between measurements and CFD results is shown for the local flow angle at several stations ahead of the wind turbine blades. For attached and moderately stalled flow conditions the thrust and torque predictions are fair, though improvements in the stalled flow regime are necessary to avoid overprediction of torque. Subsequently, the wind-tunnel wall effects on the blade aerodynamics, as well as the blade/tower interaction, were investigated. The selected case corresponded to 7 m/s up-wind wind turbine at 0 deg of yaw angle and a rotational speed of 72 rpm. The obtained results suggest that the present method can cope well with the flows encountered around wind turbines providing useful results for their aerodynamic performance and revealing flow details near and off the blades and tower.

Design and Validation of Sensor Balance for Propeller Experiment

2014 ◽  
Vol 496-500 ◽  
pp. 652-656
Author(s):  
Jun Jiao ◽  
Bi Feng Song ◽  
Yu Gang Zhang
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Experiment ◽  
Experimental Results ◽  
Measuring System ◽  
Virtual Instruments ◽  
Static Calibration ◽  
Two Component ◽  
Thrust And Torque ◽  
Measuring Force

This paper proposes a new two-component sensor balance to measure the thrust and torque of the propeller. Its principles of measuring force were derived and the procedures of balance measuring system were also provided according to the virtual instruments. The sensor balance was calibrated through the ground static calibration bench to verify its accuracy. And a ground static thrust experiment on a one-meter sized propeller model was carried out. By comparison, the experimental results of adopting the designed sensor balance basically tally with those of wind tunnel experiment, which proves that this sensor balance can be used in propeller experiments.

scholarly journals Simulation and flight experiments of a quadrotor tail-sitter vertical take-off and landing unmanned aerial vehicle with wide flight envelope

2018 ◽  
Vol 10 (4) ◽  
pp. 303-317 ◽  
Author(s):  
Ximin Lyu ◽  
Haowei Gu ◽  
Jinni Zhou ◽  
Zexiang Li ◽  
Shaojie Shen ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Unmanned Aerial Vehicle ◽  
Wind Tunnel Test ◽  
Small Scale ◽  
Level Flight ◽  
Flight Envelope ◽  
Aerial Vehicle ◽  
Attitude Controller ◽  
And Control ◽  
Thrust And Torque

This paper presents the modeling, simulation, and control of a small-scale electric powered quadrotor tail-sitter vertical take-off and landing unmanned aerial vehicle. In the modeling part, a full attitude wind tunnel test is performed on the full-scale unmanned aerial vehicle to capture its aerodynamics over the flight envelope. To accurately capture the degradation of motor thrust and torque at the presence of the forward speed, a wind tunnel test on the motor and propeller is also carried out. The extensive wind tunnel tests, when combined with the unmanned aerial vehicle kinematics model, dynamics model and other practical constraints such as motor saturation and delay, lead to a complete flight simulator that can accurately reveal the actual aircraft dynamics as verified by actual flight experiments. Based on the developed model, a unified attitude controller and a stable transition controller are designed and verified. Both simulation and experiments show that the developed attitude controller can stabilize the unmanned aerial vehicle attitude over the entire flight envelope and the transition controller can successfully transit the unmanned aerial vehicle from vertical flight to level flight with negligible altitude dropping, a common and fundamental challenge for tail-sitter vertical take-off and landing aircrafts. Finally, when supplied with the designed controller, the tail-sitter unmanned aerial vehicle can achieve a wide flight speed envelope ranging from stationary hovering to fast level flight. This feature dramatically distinguishes our aircraft from conventional fixed-wing airplanes.

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

Sensors ◽  
2021 ◽  
Vol 22 (1) ◽  
pp. 2
Author(s):  
Zbigniew Czyż ◽  
Paweł Karpiński ◽  
Krzysztof Skiba ◽  
Mirosław Wendeker
Keyword(s):  
Wind Tunnel ◽  
Electric Propulsion ◽  
Aerodynamic Performance ◽  
Force Balance ◽  
Performance Tests ◽  
Electrical Parameters ◽  
Subsonic Wind Tunnel ◽  
Propeller Performance ◽  
Propeller Geometry ◽  
Thrust And Torque

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.

scholarly journals Determining the Aerodynamic Characteristics of a Propeller-Driven Anti-UAV Fighter While Designing Air Propellers

2021 ◽  
Vol 2021 (4) ◽  
pp. 53-67
Author(s):  
Vasyl Loginov ◽  
Yevgen Ukrainets ◽  
Viktor Popov ◽  
Yevgen Spirkin
Keyword(s):  
Wind Tunnel ◽  
Numerical Methods ◽  
High Efficiency ◽  
Aerodynamic Characteristics ◽  
The Body ◽  
Physical Experiments ◽  
Thrust And Torque ◽  
Aircraft Configurations ◽  
Aerodynamic Configuration ◽  
Selection Of

Abstract Given the rising importance of unmanned aerial vehicles (UAVs), this article addresses the urgent scientific problem of determining the aerodynamic characteristics of a UAV while laying out the propellers for the wings. We discuss the methodology for experimental wind-tunnel studies of aircraft configurations with propellers. It is shown that a characteristic feature of the configuration small-elongation wing with propellers is the absence of elements that are not affected by propellers. This feature makes it difficult to implement and automate a wind tunnel experiment, since there are problems with providing similar criteria for a working propeller; it is difficult to achieve perfect balancing for solid drive propellers, which causes vibration, the level of which depends on uncontrolled factors; the inability to neglect the presence of the body elements influence to the blades of propellers; the difficulty of direct measuring propeller thrust and torque. The presented methodology involves the integrated usage of experimental and numerical methods to eliminate the difficulties in conducting physical experiments in a wind tunnel. This approach makes it possible to combine the high credibility of experimental data in the study of the physical essence of phenomena with high efficiency and accuracy in determining aerodynamic characteristics by numerical methods. Using this approach, we established dependences of the aerodynamic characteristics of the small-elongation wing configuration with counter-rotating propellers on the geometric and kinematic parameters of the configuration for other extensions and constrictions of the wings. These data can serve as the basis for the development of recommendations for the selection of sensible geometric parameters of the aerodynamic configuration of a small-elongation wing with counter-rotating propellers.

Performance and Loads of a Lift Offset Rotor: Hover and Wind Tunnel Testing

2019 ◽  
Vol 64 (2) ◽  
pp. 1-12 ◽  
Author(s):  
Christopher G. Cameron ◽  
Jayant Sirohi
Keyword(s):  
Wind Tunnel ◽  
Scale Model ◽  
Wind Tunnel Testing ◽  
Forward Flight ◽  
Maximum Increase ◽  
Bladed Rotor ◽  
Advance Ratio ◽  
Thrust And Torque ◽  
Drag Ratio ◽  
Lift To Drag Ratio

The results of hover and wind tunnel tests of a reduced-scale, model rotor operating with lift offset are presented. The two-bladed rotor had a diameter of 2.03 m and constant cross section untwisted blades. Measurements include steady and vibratory hub loads, as well as control angles and pushrod loads. The rotor system was tested in hover and at advance ratios between 0.21 and 0.53, at collective pitches ranging from 3° to 10°, achieving blade loadings in excess of 0.10. At each forward flight operating condition, sweeps of lift offset up to 15% were performed. In forward flight, the rotor effective lift-to-drag ratio was found to increase with increasing advance ratio and lift offset, with a maximum increase of 40% compared to the zero lift offset case. Vibratory loads increased with advance ratio, with the largest loads in the two- and four-per-revolution harmonics. Lift offset is shown to modify vibratory hub forces and moments transmitted to the fixed frame, increasing vibratory rolling and pitching moments while decreasing vibratory thrust and torque.

Design Considerations for Propellers in a Cavitating Environment

1978 ◽  
Vol 15 (02) ◽  
pp. 144-178 ◽  
Author(s):  
Donald L. Blount ◽  
David L. Fox
Keyword(s):  
Rational Design ◽  
Computation Time ◽  
Design Practice ◽  
Good Balance ◽  
Design Considerations ◽  
Performance Predictions ◽  
Blade Section ◽  
Selection For ◽  
Thrust And Torque ◽  
Propeller Thrust

Cavitation adds a dimension to propeller operation that necessitates rational design practice to approach a good balance of craft requirements. This paper discusses propeller characteristic format to reduce the computation time to make performance predictions and propeller selection for partially and fully cavitating conditions. In addition, maximum propeller thrust and torque loading limits are defined for four different blade section shapes, including recommended design limits. Discussers Jim W. Bordeaux Mark Oaks

scholarly journals Experimental Study on the Influence of Water and Cavitation on Propeller Load during Ice-Propeller Milling

2021 ◽  
Vol 11 (24) ◽  
pp. 11578
Author(s):  
Pei Xu ◽  
Chao Wang ◽  
Liyu Ye
Keyword(s):  
Tangential Force ◽  
Milling Process ◽  
Water Ice ◽  
Test Platform ◽  
Influence Of Water ◽  
Bearing Force ◽  
Combined Action ◽  
Ice Water ◽  
Thrust And Torque ◽  
Propeller Thrust

When the ice-class propeller sails in an icy sea, it is affected by external factors such as water, ice, and cavitation, and the process of mutual interference is extremely complicated. In order to study the influence of water and cavitation on propeller load during the ice-propeller milling process, a test platform for ice–water propeller milling action was constructed. The load and cavitation of the propeller and single blade were measured during ice-propeller milling in air and water (atmospheric pressure and decompression conditions). Simultaneously, the changes in the load and bearing force of the propeller and blade were studied at different working conditions. The results show that, in the process of ice–water propeller milling, the direction of the propeller thrust generated by the water is opposite to that of the axial force generated by ice; the combined action of the two causes propeller thrust loss, whereas the combined action of water and ice increases propeller torque. The presence of water increases the thrust, torque, and bearing force of the fluctuating amplitude of the blade. The occurrence of cavitation reduces the thrust and torque of the propeller and blade and increases thrust fluctuating amplitudes while decreasing the tangential force fluctuating amplitude of the blade.

Gap Effect on Performance of Podded Propulsors in Straight-Ahead and Azimuthing Conditions

2010 ◽  
Vol 47 (01) ◽  
pp. 47-58
Author(s):  
Mohammed F. Islam ◽  
Brian Veitch ◽  
Pengfei Liu ◽  
Ayhan Akinturk
Keyword(s):  
Open Water ◽  
Operating Conditions ◽  
Gap Effect ◽  
Axial Distance ◽  
Noticeable Effect ◽  
Podded Propulsor ◽  
Propeller Performance ◽  
Thrust And Torque ◽  
Straight Ahead ◽  
Propeller Thrust

This paper presents results of an experimental study on the effect of gap distance on propulsive characteristics of puller and pusher podded propulsors in straight-ahead and static azimuthing open-water conditions. The gap distance is the axial distance between the rotating (propeller) and stationary (pod) parts of a podded propulsor. The propeller thrust and torque, unit forces, and moments in the three-coordinate directions of a model podded unit were measured using a custom-designed pod dynamometer in various operating conditions. The model propulsor was tested at the gap distances of 0.3%, 1%, and 2% of propeller diameter for a range of advance coefficients combined with the range of static azimuthing angles from +20_ to 20_ with a 10_ increment. The tests were conducted both in puller and pusher configurations in the same loading and azimuthing conditions. In the puller configuration, the gap distance did not have any noticeable effect on propeller torque in straight course condition, but had an effect in azimuthing conditions. The propeller thrust and efficiency were also influenced by the change of gap distance, and the effects were more pronounced at high azimuthing angles and high advance coefficients. For pusher configuration, however, the gap distance did not affect the propeller performance characteristics in straight-ahead and azimuthing conditions. Both in straight course and azimuthing conditions, the unit thrust and efficiency were not influenced by the gap distance in either puller or pusher configurations. The gap distance had a noticeable effect on unit transverse force and steering moment both in puller and pusher configurations, and both in straight course

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