Survey of multi-wire probe data processing techniques and efficient processing of four-wire probe velocity measurements in turbulent flows

Maciel, Yvan; Gleyzes, C.

doi:10.1007/s003480050428

Cited by 9 publications

(4 citation statements)

References 34 publications

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“…Hence the present investigation is undertaken to develop a computationally less intensive method to process data from five hole probes, namely lookup table method. Similar methods are developed by Lueptow et al [3] for a two sensor hot wire probe, Maciel and Gleyzes [4] for a four sensor hot wire probe and Wenger and Devenport [5] for a seven hole probe.…”

Section: Technical Notementioning

confidence: 95%

Look Up Table Method for Five Hole Probe Data Reduction

Sitaram,

Suresh,

Kumar

et al. 2023

joast

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A lookup method for extracting flow field information from five hole probe measurements is presented. The look up table method consists of two step interpolation. In the first step, the calibration space is divided into a large number of small intervals of yaw and pitch coefficients (0.1, 0.05 or 0.01) and the required quantities are interpolated using local cubic spline interpolation technique. The interpolated values are stored in a large square matrix. In the second step, the measured values of yaw and pitch coefficients are used to determine yaw and pitch angles by linear interpolation. Same procedure is used to determine total and static pressure coefficients. Additional data taken during the calibration is used for validating lookup table method and spline interpolation method. The errors from the look up table method, particularly with the interval of 0.01 are about the same or lower than those obtained from the spline interpolation method. The computational times for lookup table method are found to be lower than that for the spline interpolation method. The lookup table method seems to be attractive when a large amount of five hole probe data is to be processed and in cases where online data processing is required.

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Section: Technical Notementioning

confidence: 95%

Look Up Table Method for Five Hole Probe Data Reduction

Sitaram,

Suresh,

Kumar

et al. 2023

joast

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“…5% and the flow deflections in the order of one tenth of a degree or less. It has to be considered that these small values are comparable with the accuracy of the measurement technique (13) . Similarly, the action of the rotors and has been mounted on a special displacement unit, which allowed an adjustment of the view from the infrared computer via remote control and more than one measurement at a data point at different regions of the model.…”

Section: Inflow Hotwire Measurementsmentioning

confidence: 99%

On the generation of a helicopter aerodynamic database

Raffel

Gregorio²,

Groot³

et al. 2011

Aeronaut. j.

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NOMENCLATURE a speed of sound, ms -1 c blade chord, m u′ 2 root mean square of velocitiy longitudinal component v′ 2 root mean square of velocitiy spanwise component w′ 2 root mean square of velocitiy vertical component M WT Mach number of wind-tunnel flow, M WT = V WT /a M MR Mach number of blade tip in hover, main rotor, M MR = (ΩR) MR /a M TR Mach number of blade tip in hover, tail rotor, M TR = (ΩR) TR /a R blade radius, m α S rotor shaft angle-of-attack α fus fuselage angle-of-attack μ advance ratio M WT /M MR ψ MR main rotor azimuth angle (0° = reference blade above the fuselage) Ω rotor rotational frequency, rad/s ABSTRACT The GOAHEAD (Generation of an Advanced Helicopter Experimental Aerodynamic Database for CFD code validation) consortium was created in the frame of an EU-project in order to create an experimental database for the validation of 3D-CFD and comprehensive aeromechanics methods for the prediction of unsteady viscous flows. This included the rotor dynamics for complete helicopter configurations, i.e. main rotor -fuselage -tail rotor configurations with emphasis on viscous phenomena like flow separation and transition from laminar to turbulent flow. The wind tunnel experiments have been performed during two weeks in the DNW-LLF on a Mach-scaled model of a modern transport helicopter consisting of the main rotor, the fuselage, control surfaces and the tail rotor. For the sake of controlled boundary conditions for later CFD validation, a closed test section has been used. The measurement comprised global forces of the main rotor and the fuselage, steady and unsteady pressures, transition positions, stream lines, position of flow separation, velocity profiles at the test section inlet, velocity fields in the model wake, vortex trajectories and elastic deformations of the main and tail rotor blades.

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“…Two sensor probe signal analysis is given in the papers [3][4][5][6][7]15,16]. Various analytical methods for triple or more sensors are given in the papers [7][8][9][10][11][12][13][14]16]. All these methods are based on curve or surface fitting in the space of calibration points.…”

Section: Introductionmentioning

confidence: 99%