A novel calibration algorithm for five-hole pressure probe

Paul, Akshoy Ranjan; Upadhyay, Ravi Ranjan; Jain, Anuj

doi:10.4314/ijest.v3i2.68136

Cited by 28 publications

(10 citation statements)

References 5 publications

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“…When, for example, hole number 1, an outer hole, is measuring the highest pressure, the reading from hole number 3, opposite to number 1, is ignored in the creation of the pressure coefficient. Paul et al (2011) have modified this approach to include the central hole pressure in all sectors.…”

Section: Calibrationmentioning

confidence: 99%

A compact in-blade five hole pressure probe for local inflow study on a horizontal axis wind turbine

Moscardi

Johnson

2016

Wind Engineering

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Understanding local inflow conditions on a wind turbine blade on an operating wind turbine can further understanding of aerodynamic variations and help predict loads on the turbine. Turbine blades are generally designed with a two-dimensional steady approach, however the real wind conditions are highly three-dimensional (3D) and unsteady. Detailed measurements are not common for validating aerodynamic models. The aim of this theoretical and experimental study is to build, calibrate, install and test a compact in-blade five hole pressure probe system to be used to retrieve these measurements. Wind tunnel calibration of the five hole pressure probe has been successfully completed using an automated traversing system over a ±45° range, with 5° increments. Error analysis showed that the multi-zone pressure coefficient data reduction approach is the most suitable for this application. This approach not only extends the measurable local inflow angles up to ±70°, but also it allows any reference pressure for differential pressure readings. A new data acquisition system (DAQ) internal to a rotating small wind turbine blade section was developed. Space limitations resulted in a custom built DAQ of very contained dimensions. This included, among others, five pressure transducers on a printed circuit board, a 16 bit analog to digital converter, an Arduino microcontroller, and a Bluetooth transceiver to transmit the data wirelessly to the main computer. The new blade section was designed and 3D-printed in such a way that the DAQ instrumentation could be easily accessed and, at the same time, had an acceptable structural solidity. A series of tests were conducted on a 3.4 m diameter wind turbine in a large scale wind tunnel in order to assess the correct functioning of the probe system. As expected, the inflow measurement obtained while the turbine was operating under yawed conditions showed a periodically oscillating inflow vector. The period of this variation was the same as the period of the rotor rotation.

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Section: Calibrationmentioning

confidence: 99%

A compact in-blade five hole pressure probe for local inflow study on a horizontal axis wind turbine

Moscardi

Johnson

2016

Wind Engineering

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“…The data collected was processed using a method based upon the work of Lee and Wood 13 and Paul, et al 14 The original methods broke the pitch-yaw space of the probe into various regions based upon the differences between pairs of holes. This was made more robust by including additional overlaps in the regions to eliminate the potential for hysteresis.…”

Section: B Two-element 5-hole Probe Rakementioning

confidence: 99%

Computational and Experimental Evaluation of a Complex Inlet Swirl Pattern Generation System

Sanders¹,

Nessler²,

Copenhaver³

et al. 2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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An assessment was conducted to determine the suitability of subscale, low-Mach-number, particle image velocimetry (PIV) testing and computational fluid dynamics (CFD) analysis to evaluate swirling flow downstream of a swirl pattern generation system composed of continuous patterns of turning vanes. Successful demonstration of the evaluation methods required acceptable comparison of the PIV and CFD to an independent five-hole probe measurement performed at the design Mach number and full-scale geometry. The focus of the investigation was on direct comparison of flow angles and flow features one diameter downstream of the swirl pattern generator. Both the subscale PIV and the CFD provide adequate representation of the swirling flow produced by the full-scale generator. The subscale PIV and CFD may be used to predict the performance of the full-scale swirl pattern generator and allow for inexpensive testing and analysis to be performed during the design process, thus improving the accuracy of generating a desired swirl pattern.

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“…Then, the ratio of the hole diameter to the tip diameter is 0.16. Although this ratio is relatively small compared to the one in [6], the number is fairly close to newer designs, such as those in [39] and [41].…”

Section: Probe Design and Manufacturingmentioning

confidence: 78%

Development and Modeling of a Low-Cost Unmanned Aerial Vehicle Research Platform

Arifianto

Farhood

2014

J Intell Robot Syst

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This paper describes the development and modeling of a low-cost and reliable small unmanned aerial vehicle research platform for advanced control implementation. The platform is mostly constructed of low-cost commercial-off-the-shelf (COTS) components. The only non-COTS components are the airdata probes, which are manufactured and calibrated in-house. The airframe used is the commercially available radio-controlled (R/C) 6-foot Telemaster airplane from Hobby Express, chosen mainly for its adequately spacious fuselage and for being reasonably stable and sufficiently agile. One noteworthy feature of this platform is the use of two separate low-cost onboard computers for handling the data management/hardware interfacing and control computation. Specifically, the single board computer, Gumstix Overo Fire, is used to execute the control algorithms, whereas the open source autopilot, Ardupilot Mega, is mostly used to interface the Overo computer with the sensors and actuators. The platform supports multi-vehicle operations through the use of a radio modem that enables multi-point communications. As the goal of this platform is to implement rigorous control algorithms for real-time trajectory tracking and distributed control, it O. Arifianto · M. Farhood ( ) is important to derive an appropriate flight dynamic model of the platform, based on which the controllers will be synthesized. For that matter, the paper provides reasonably accurate models of the vehicle, servomotors, and propulsion system. Namely, the output error method is used to estimate the longitudinal and lateraldirectional aerodynamic parameters from flight test data. The moments of inertia of the platform are determined using the simple pendulum test method, and the frequency response of each servomotor is also obtained experimentally. The Javaprop applet is used to obtain lookup tables relating airspeed to propeller thrust at constant throttle settings.

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A novel calibration algorithm for five-hole pressure probe

Cited by 28 publications

References 5 publications

A compact in-blade five hole pressure probe for local inflow study on a horizontal axis wind turbine

A compact in-blade five hole pressure probe for local inflow study on a horizontal axis wind turbine

Computational and Experimental Evaluation of a Complex Inlet Swirl Pattern Generation System

Development and Modeling of a Low-Cost Unmanned Aerial Vehicle Research Platform

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