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Journal articles on the topic 'Pitot-static Measurements'

Author: Grafiati

Published: 4 June 2021

Last updated: 2 February 2022

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1

Moum, James N. "Ocean Speed and Turbulence Measurements Using Pitot-Static Tubes on Moorings." Journal of Atmospheric and Oceanic Technology 32, no. 7 (2015): 1400–1413. http://dx.doi.org/10.1175/jtech-d-14-00158.1.

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AbstractA low-power (<10 mW), physically small (15.6 cm long × 3.2 cm diameter), lightweight (600 g Cu; alternatively, 200 g Al), robust, and simply calibrated pitot-static tube to measure mean speed and turbulence dissipation is described and evaluated. The measurement of speed is derived from differential pressure via Bernoulli’s principle. The differential pressure sensor employed here has relatively small, but significant, adverse sensitivities to static pressure, temperature, and acceleration, which are characterized in tests in the college’s laboratory. Results from field tests on moo

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2

Turkmen, Ilke. "An alternative neural airspeed computation method for aircrafts." Aircraft Engineering and Aerospace Technology 90, no. 2 (2018): 368–78. http://dx.doi.org/10.1108/aeat-10-2015-0228.

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Purpose This paper aims to present an alternative airspeed computation method based on artificial neural networks (ANN) without requiring pitot-static system measurements. Design/methodology/approach The data set used to train proposed neural model is obtained from the Digital Flight Data Acquisition Unit records of a Boeing 737 type commercial aircraft for real flight routes. The proposed method uses the flight parameters as inputs of the ANN. The Levenberg–Marquardt training algorithm was used to train the neural model. Findings The predicted airspeed values obtained with ANN are in good agr

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Rautenberg, Alexander, Martin Graf, Norman Wildmann, Andreas Platis, and Jens Bange. "Reviewing Wind Measurement Approaches for Fixed-Wing Unmanned Aircraft." Atmosphere 9, no. 11 (2018): 422. http://dx.doi.org/10.3390/atmos9110422.

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One of the biggest challenges in probing the atmospheric boundary layer with small unmanned aerial vehicles is the turbulent 3D wind vector measurement. Several approaches have been developed to estimate the wind vector without using multi-hole flow probes. This study compares commonly used wind speed and direction estimation algorithms with the direct 3D wind vector measurement using multi-hole probes. This was done using the data of a fully equipped system and by applying several algorithms to the same data set. To cover as many aspects as possible, a wide range of meteorological conditions

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Kilic, Ugur, and Gulay Unal. "Aircraft air data system fault detection and reconstruction scheme design." Aircraft Engineering and Aerospace Technology 93, no. 6 (2021): 1104–14. http://dx.doi.org/10.1108/aeat-01-2021-0018.

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Purpose The purpose of this study is to detect and reconstruct a fault in pitot probe and static ports, which are components of the air data system in commercial aircrafts, without false alarm and no need for pitot-static measurements. In this way, flight crew will be prevented from flying according to incorrect data and aircraft accidents that may occur will be prevented. Design/methodology/approach Real flight data collected from a local airline was used to design the relevant system. Correlation analysis was performed to select the data related to the airspeed and altitude. Fault detection

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Cooper, W. A., S. M. Spuler, M. Spowart, D. H. Lenschow, and R. B. Friesen. "Calibrating airborne measurements of airspeed, pressure and temperature using a Doppler laser air-motion sensor." Atmospheric Measurement Techniques 7, no. 9 (2014): 3215–31. http://dx.doi.org/10.5194/amt-7-3215-2014.

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Abstract. A new laser air-motion sensor measures the true airspeed with a standard uncertainty of less than 0.1 m s−1 and so reduces uncertainty in the measured component of the relative wind along the longitudinal axis of the aircraft to about the same level. The calculated pressure expected from that airspeed at the inlet of a pitot tube then provides a basis for calibrating the measurements of dynamic and static pressure, reducing standard uncertainty in those measurements to less than 0.3 hPa and the precision applicable to steady flight conditions to about 0.1 hPa. These improved measurem

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6

Laitón, Sergio Nicolas Pachón, João Felipe de Araujo Martos, Israel da Silveira Rego, George Santos Marinho, and Paulo Gilberto de Paula Toro. "Experimental Study of Single Expansion Ramp Nozzle Performance Using Pitot Pressure and Static Pressure Measurements." International Journal of Aerospace Engineering 2019 (February 27, 2019): 1–11. http://dx.doi.org/10.1155/2019/7478129.

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In order to overcome the drag at hypersonic speed, hypersonic flight vehicles require a high level of integration between the airframe and the propulsion system. Propulsion system based on scramjet engine needs a close interaction between its aerodynamics and stability. Hypersonic vehicle nozzles which are responsible for generating most of the thrust generally are fused with the vehicle afterbody influencing the thrust efficiency and vehicle stability. Single expansion ramp nozzles (SERN) produce enough thrust necessary to hypersonic flight and are the subject of analysis of this work. Flow e

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7

Hüning, Marcus. "Discharge coefficient measurements of round, inclined orifices with inlet cross-flow in and against direction of inclination." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 227, no. 6 (2012): 1266–79. http://dx.doi.org/10.1177/0954406212456476.

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In an effort to improve the validated understanding of aerodynamic losses across orifices, this publication describes discharge coefficient measurements, derived from a specially designed test rig. This rig contains a straight, square section main channel (20 × 20 mm2) with exchangeable orifice plates at one side wall with 7 mm hole diameters. The channel was supplied with compressed air at between about zero velocity and nearly the speed of sound. Static pressure ratios across orifices were varied between 1.05 and 2 in addition. Test orifices had inclinations of 0°, 30° and 60° in and against

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8

Ariante, Gennaro, Salvatore Ponte, Umberto Papa, and Giuseppe Del Core. "Estimation of Airspeed, Angle of Attack, and Sideslip for Small Unmanned Aerial Vehicles (UAVs) Using a Micro-Pitot Tube." Electronics 10, no. 19 (2021): 2325. http://dx.doi.org/10.3390/electronics10192325.

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Fixed and rotary-wing unmanned aircraft systems (UASs), originally developed for military purposes, have widely spread in scientific, civilian, commercial, and recreational applications. Among the most interesting and challenging aspects of small UAS technology are endurance enhancement and autonomous flight; i.e., mission management and control. This paper proposes a practical method for estimation of true and calibrated airspeed, Angle of Attack (AOA), and Angle of Sideslip (AOS) for small unmanned aerial vehicles (UAVs, up to 20 kg mass, 1200 ft altitude above ground level, and airspeed of

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9

Subramanian, Chelakara S., Nagahiko Shinjo, and Sathya N. Gangadharan. "A Study of Hydrodynamic Characteristics of Boundary Layer With Algae Roughness." Marine Technology and SNAME News 41, no. 02 (2004): 60–66. http://dx.doi.org/10.5957/mt1.2004.41.2.60.

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Filamentous algae fouling, such as Enteromorpha clathrata, is a soft and hairylike roughness that sometimes grows even thicker than a normal boundary layer. Typically, such fouling has been treated as traditional roughness functions to yield hydrodynamic characteristics. This technique has been successfully used for a thin fouling layer. However, it may not be applicable on a thicker layer, as the present study found substantial fluid flow within the layer. For such cases, the roughness cannot be treated simply as a passive geometric variable, but its kinematics and interactions with the flow

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10

Granzoto, R. M., L. A. Algodoal, G. J. Zambrano, and G. G. Becker. "Horizontal tail local angle-of-attack and total pressure measurements through static pressure ports and Kiel pitot." Aeronautical Journal 123, no. 1268 (2019): 1476–91. http://dx.doi.org/10.1017/aer.2019.68.

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ABSTRACTAircraft handling qualities may be influenced by wing-tip flow separations and horizontal tail (HT) reduced efficiency caused by loss of local dynamic pressure or local tailplane flow separations in high angle-of-attack manoeuvres. From the flight tester’s perspective, provided that the test aircraft presents sufficient longitudinal control authority to overcome an uncommanded nose-up motion, this characteristic should not be a safety factor. Monitoring and measuring the local airflow in the aircraft’s HT provides information for safe flight-test envelope expansion and data for early a

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11

Cooper, W. A., S. M. Spuler, M. Spowart, D. H. Lenschow, and R. B. Friesen. "Calibrating airborne measurements of airspeed, pressure and temperature using a Doppler laser air-motion sensor." Atmospheric Measurement Techniques Discussions 7, no. 3 (2014): 2585–630. http://dx.doi.org/10.5194/amtd-7-2585-2014.

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Abstract. A new laser air-motion sensor measures the true airspeed with an uncertainty of less than 0.1 m s−1 (standard error) and so reduces uncertainty in the measured component of the relative wind along the longitudinal axis of the aircraft to about the same level. The calculated pressure expected from that airspeed at the inlet of a pitot tube then provides a basis for calibrating the measurements of dynamic and static pressure, reducing standard-error uncertainty in those measurements to less than 0.3 hPa and the precision applicable to steady flight conditions to about 0.1 hPa. These im

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12

Jangir, Ravirai, Nekkanti Sitaram, and Ct Gajanan. "A Miniature Four-Hole Probe for Measurement of Three-Dimensional Flow with Large Gradients." International Journal of Rotating Machinery 2014 (2014): 1–12. http://dx.doi.org/10.1155/2014/297861.

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A miniature four-hole probe with a sensing area of 1.284 mm2to minimise the measurement errors due to the large pressure and velocity gradients that occur in highly three-dimensional turbomachinery flows is designed, fabricated, calibrated, and validated. The probe has good spatial resolution in two directions, thus minimising spatial and flow gradient errors. The probe is calibrated in an open jet calibration tunnel at a velocity of 50 m/s in yaw and pitch angles range of ±40 degrees with an interval of 5 degrees. The calibration coefficients are defined, determined, and presented. Sensitivit

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Wagner, Alexander, Erich Schülein, René Petervari, et al. "Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels by means of a slender wedge probe and direct numerical simulation." Journal of Fluid Mechanics 842 (March 13, 2018): 495–531. http://dx.doi.org/10.1017/jfm.2018.132.

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Combined free-stream disturbance measurements and receptivity studies in hypersonic wind tunnels were conducted by means of a slender wedge probe and direct numerical simulation. The study comprises comparative tunnel noise measurements at Mach 3, 6 and 7.4 in two Ludwieg tube facilities and a shock tunnel. Surface pressure fluctuations were measured over a wide range of frequencies and test conditions including harsh test environments not accessible to measurement techniques such as Pitot probes and hot-wire anemometry. A good agreement was found between normalized Pitot pressure fluctuations

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14

Raupach, MR, and JF Leys. "Aerodynamics of a portable wind erosion tunnel for measuring soil erodibility by wind." Soil Research 28, no. 2 (1990): 177. http://dx.doi.org/10.1071/sr9900177.

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Portable wind erosion tunnels must satisfy several aerodynamic criteria to ensure that the flow within them acceptably reproduces the atmospheric flow causing natural wind erosion. We define these criteria and use them to assess the flow and turbulence in two alternative designs of portable wind erosion tunnel: the first has a working section with an approximately triangular, 'tent-shaped' cross section, while the second has a conventional, rectangular working section. The measurements were made with Pitot-static tubes and X-configuration hot-wire anemometers, over stable (non-eroding) rough s

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15

Traub, L. W. "Estimating aerofoil lift from flow angle." Aeronautical Journal 119, no. 1219 (2015): 1167–73. http://dx.doi.org/10.1017/s0001924000011180.

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Estimation of the lift of an aerofoil is one of the fundamental measurements of fluid mechanics. Lift is commonly measured using a load cell or a force balance. Non-intrusive methods to measure lift are usually pressure based. Aerofoils may be pressure tapped where small surface orifices are connected via tubing to a pressure measurement system, either a multi-tube manometre or an electronic system. Both measurement options add cost and complication, especially in an educational setting. Pressure tapping small aerofoils can also be difficult, especially if the models are rapid prototyped (RP).

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16

Lee, K.-H., T. Setoguchi, S. Matsuo, and H.-D. Kim. "An experimental study of underexpanded sonic, coaxial, swirl jets." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 218, no. 1 (2004): 93–103. http://dx.doi.org/10.1243/095440604322786974.

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The present study addresses experimental investigations of the near-field flow structures of an underexpanded sonic, dual, coaxial, swirl jet. The swirl stream is discharged from the secondary annular nozzle and the primary inner nozzle provides the underexpanded free jets. The interactions between the secondary swirl and primary underexpanded jets are quantified by a fine pitot impact and static pressure measurements and are visualized using a shadowgraph optical method. The pressure ratios of the secondary swirl and primary underexpanded jets are varied below 7.0. Experiments are conducted t

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Dufresne, Nathaniel P., and Martin Wosnik. "Velocity Deficit and Swirl in the Turbulent Wake of a Wind Turbine." Marine Technology Society Journal 47, no. 4 (2013): 193–205. http://dx.doi.org/10.4031/mtsj.47.4.20.

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AbstractEnergy production data from several of the existing large offshore wind farms indicate that turbine arrays can suffer from a significant overall energy production shortfall, due to wakes generated by turbines upstream interacting with turbines downstream. An experimental investigation of the axial and azimuthal (swirl) velocity field in the wake of a single three-bladed wind turbine with rotor diameter of 0.91 m was conducted. The turbine was positioned in the free stream, near the entrance of the 6 m×2.7 m cross section of the UNH Flow Physics Facility, a 72-m-long boundary layer wind

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18

Lubbock, RJ, and MLG Oldfield. "Turbulent velocity and pressure fluctuations in gas turbine combustor exit flows." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 4 (2017): 337–49. http://dx.doi.org/10.1177/0957650917732885.

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This paper presents the results of two test programmes using novel instrumentation to characterise the pressure and turbulent velocity fields in gas-turbine combustor exit flows. The probes are uncooled, therefore a fast-insertion traverse system is employed to prevent thermal degradation of the instrumentation in these severely hostile high-temperature environments. High-bandwidth ultra-miniature pressure transducers are used to measure unsteady total pressure, whilst a Pitot tube is employed to measure time-averaged total pressure. The probes are 4 mm in diameter with a measurement bandwidth

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19

Alaoui-Sosse, Sara, Pierre Durand, Patrice Medina, Philippe Pastor, Marie Lothon, and Iuri Cernov. "OVLI-TA: An Unmanned Aerial System for Measuring Profiles and Turbulence in the Atmospheric Boundary Layer." Sensors 19, no. 3 (2019): 581. http://dx.doi.org/10.3390/s19030581.

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In recent years, we developed a small, unmanned aerial system (UAS) called OVLI-TA (Objet Volant Leger Instrumenté–Turbulence Atmosphérique) dedicated to atmospheric boundary layer research, in Toulouse (France). The device has a wingspan of 2.60 m and weighed 3.5 kg, including payload. It was essentially developed to investigate turbulence in a way complementary to other existing measurement systems, such as instrumented towers/masts. OVLI-TA’s instrumental package includes a 5-hole probe on the nose of the airplane to measure attack and sideslip angles, a Pitot probe to measure static pressu

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20

Eng, J., A. Gomez, and S. Mink. "Insensitivity of maximum expiratory flow to bronchodilation in normal dogs." Journal of Applied Physiology 68, no. 5 (1990): 2006–12. http://dx.doi.org/10.1152/jappl.1990.68.5.2006.

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We examined the effects of the inhaled parasympatholytic agent atropine and the sympathomimetic agent salbutamol on partitioned frictional pressure (Pfr) losses to the site of flow limitation (choke point, CP) in dogs to see how changes brought about by these agents would affect maximum expiratory flow (Vmax) and response to breathing 80% He-20% O2 (delta Vmax) in terms of wave-speed theory of flow limitation. In open-chest dogs, a Pitot-static tube was advanced down the right lower lobe to locate CP, to determine CP lateral and end-on pressures (PE), and to partition the airway into periphera

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Greville, H. W., M. E. Arnup, S. N. Mink, L. Oppenheimer, and N. R. Anthonisen. "Mechanism of reduced maximum expiratory flow in dogs with compensatory lung growth." Journal of Applied Physiology 60, no. 2 (1986): 441–48. http://dx.doi.org/10.1152/jappl.1986.60.2.441.

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We examined the mechanism of the reduced maximum expiratory flow rates (Vmax) in a dog model of postpneumonectomy compensatory lung growth. During forced expiration, a Pitot-static tube was used to locate the airway site of flow limitation, or choke point, and to measure dynamic intrabronchial pressures. The factors determining Vmax were calculated and the results analyzed in terms of the wave-speed theory of flow limitation. Measurements were made at multiple lung volumes and during ventilation both with air and with HeO2. Five of the puppies had undergone a left pneumonectomy at 10 wk of age

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Wünsche, Jens N., and John W. Palmer. "Portable Through-flow Cuvette System for Measuring Whole-canopy Gas Exchange of Apple Trees in the Field." HortScience 32, no. 4 (1997): 653–58. http://dx.doi.org/10.21273/hortsci.32.4.653.

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A monitoring and control system for sequentially measuring whole-tree-canopy gas exchange of four apple (Malus domestica Borkh.) trees in the field is described. A portable, highly transparent, open-top whole-canopy cuvette was developed for complete enclosure of the above-ground portion of the tree. The flux of whole-canopy CO2 and H2 0 vapor was estimated from differential CO2 concentration and H2O-vapor partial pressure between ambient/reference air entering the cuvette and analysis air leaving the cuvette, as measured by infrared gas analysis. The bulk air-flow rate through the chamber was

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Young, J. B. "Condensation in Jet Engine Intake Ducts During Stationary Operation." Journal of Engineering for Gas Turbines and Power 117, no. 2 (1995): 227–36. http://dx.doi.org/10.1115/1.2814085.

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The paper describes an analysis of the condensation of moist air in very long intake ducts of jet engines during stationary operation. Problems arising from such condensation include fan overspeed and increased stagnation pressure loss in the intake duct. The analysis demonstrates that, for moderate values of relative humidity, homogeneous condensation will occur in an outer annulus adjacent to the intake cowling if the local flow Mach number attains values of about 1.0. In the central region of the intake duct, where design Mach numbers of 0.8 may be attained, homogeneous condensation is unli

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Li, S. M., T. L. Chu, Y. S. Yoo, and W. F. Ng. "Transonic and Low Supersonic Flow Losses of Two Steam Turbine Blades at Large Incidences." Journal of Fluids Engineering 126, no. 6 (2004): 966–75. http://dx.doi.org/10.1115/1.1839927.

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A linear cascade experiment was conducted to investigate transonic and low supersonic flow losses of two nozzle blades for the steam turbines. In the experiment, flow incidences were changed from −34° to 35° and exit Mach numbers were varied from 0.60 to 1.15. Tests were conducted at Reynolds numbers between 7.4×105 and 1.6×106. Flow visualization techniques, such as shadowgraph, Schlieren, and surface color oil were used to document the flows. Measurements were made by using downstream traverses with Pitot probe, upstream total pressure probe, and sidewall static pressure taps. The losses wer

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B.T., Kannan, and Panchapakesan N.R. "Effect of momentum flux distribution on multiple round jets." Aircraft Engineering and Aerospace Technology 90, no. 2 (2018): 452–60. http://dx.doi.org/10.1108/aeat-11-2016-0233.

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Purpose This study aims to investigate the effects of nozzle momentum flux distribution on the flow field characteristics. Design/methodology/approach The nozzle configuration consists of a central nozzle surrounded by four nozzles. All nozzles have the same diameter and constant separation between nozzles. OpenFOAM® is used for simulating the jet flow. Reynolds-averaged Navier-Stokes (RANS) equations are solved iteratively with a first-order closure for turbulence. Pitot-static tube with differential pressure transducer is used for mean velocity measurements. The comparison of computed result

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Gratton, G. B. "Use of Global Positioning System velocity outputs for determining airspeed measurement error." Aeronautical Journal 111, no. 1120 (2007): 381–88. http://dx.doi.org/10.1017/s0001924000004632.

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Abstract Several methods have been derived since the advent of GPS (Global Positioning System) receivers in aircraft cockpits by which these receivers may be used to calibrate these aircraft’s other instrumentation; in particular the pitot-static system. This paper presents the four most suitable methods, two of which have been developed by the author. These methods are shown with a common symbology, and their strengths, weaknesses, analysis and operational use are compared.

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Kadhim, Wael, Dhirgham Alkhafagiy, and Andrew Shires. "Simulation of the flow inside an annular can combustor." International Journal of Engineering & Technology 3, no. 3 (2014): 357. http://dx.doi.org/10.14419/ijet.v3i3.2499.

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In the gas turbine combustion system, the external flows in annuli play one of the key roles in controlling pressure loss, air flow distribution around the combustor liner, and the attendant effects on performance, durability, and stability. This paper describes a computational fluid dynamics (CFD) simulation of the flow in the outer annulus of a can combustor. Validating this simulation was done with experimental results obtained from analyzing the flow inside a can combustor annulus that was used in a Babylon/Iraq gas turbine power station. Pitot static tubes were used to measure the velocit

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Ariafar, Kavous, Thomas Cochrane, Ray Malpress, and David Buttsworth. "Pitot and static pressure measurement and CFD simulation of a co-flowing steam jet." Experimental Thermal and Fluid Science 97 (October 2018): 36–47. http://dx.doi.org/10.1016/j.expthermflusci.2018.04.004.

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Nordin, Normayati, Zainal Ambri Abdul Karim, Safiah Othman, and Vijay R. Raghavan. "Design and Development of Low Subsonic Wind Tunnel for Turning Diffuser Application." Advanced Materials Research 614-615 (December 2012): 586–91. http://dx.doi.org/10.4028/www.scientific.net/amr.614-615.586.

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In practice, it is basically difficult even with controlled measurement environment to acquire a steady, uniform and fully developed flow. The flow entering diffuser was severely distorted despite a sufficient hydrodynamic entrance length already introduced. This was mainly due to the imperfect joining of duct and the abrupt change of the inlet cross-section applied. In this study, several basic features of a low subsonic wind tunnel, i.e. a centrifugal blower with 3-phase inverter, a settling chamber, screens and a contraction cone, are designed and developed for a turning diffuser applicatio

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Yi, Wei, Jingwen Guo, Yi Fang, Renhao Qu, Siyang Zhong, and Xin Zhang. "A flow and acoustic facility for characterization of liner and meta-acoustic surfaces under grazing flow condition." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 3 (2021): 3187–93. http://dx.doi.org/10.3397/in-2021-2324.

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The Hong Kong University of Science and Technology (HKUST) has designed and assembled a new facility, a grazing flow tube, for aeroacoustic characteristics measurement of acoustic liners, e.g. transmission loss, impedance, etc., under a high-speed grazing flow. The cross-section of the test section of the tube has a dimension of 50 mm × 50 mm, and the grazing flow speed can be up to 0.3 Ma. A settling chamber, a long-enough flow development section and a multi-stage anechoic termination are adopted to ensure the high-quality flow field and acoustic field. This paper presents the detailed desig

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S.P., Setyo Hariyadi, Setiyo Setiyo, and Supriadi Supriadi. "Separasi dan Reattachment Aliran di Belakang Gundukan (Bump) Setengah Lingkaran, Segitiga dan Persegi Panjang." Jurnal Penelitian 2, no. 4 (2017): 254–60. http://dx.doi.org/10.46491/jp.v2e4.60.254-260.

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 Characteristic of viscous flow through a contour always become the interesting topic to be studied. This research studied characteristic of turbulent viscous flow through a flat plate mounted by bump. Target of this research is to know the flow characteristic through the semicircle, triangle and quadrangular bump, and also to get distribution coefficient of pressure (Cp), separation point, coefficient of pressure drag (CDp) and coefficient of total drag (CD). Beside that, in this research also conduct smoke visualization to know visualization of turbulent viscous flow through a flat pla

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Eckerle, W. A., H. Sheibani, and J. Awad. "Experimental Measurement of the Vortex Development Downstream of a Lobed Forced Mixer." Journal of Engineering for Gas Turbines and Power 114, no. 1 (1992): 63–71. http://dx.doi.org/10.1115/1.2906308.

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An experimental study was conducted to investigate the mixing processes downstream of a forced mixer. A forced mixer generates large-scale, axial (stirring) vorticity, which causes the primary and secondary flow to mix rapidly with low loss. These devices have been successfully used in the past where enhanced mixing of two streams was a requirement. Unfortunately, details of the mixing process associated with these lobed forced mixers are not well understood. Performance sensitivity to design variables has not been documented. An experiment was set up to investigate the mixing processes downst

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Soldatkin, V. M., V. V. Soldatkin, A. V. Nikitin, and G. P. Sokolova. "Ensuring Dynamic Accuracy of Aircraft’s Air Data System with Motionless Flush-Mounted Receiver of Flow." Mekhatronika, Avtomatizatsiya, Upravlenie 21, no. 9 (2020): 535–43. http://dx.doi.org/10.17587/mau.21.535-543.

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The article views, that draw-backs of aircraft’s traditional air data systems (ADS), built based installed in incoming air flow and installed outside the fuselage the pitot tube booms, temperature braking receivers, vane sensors of incidence angle and gliding angle are eliminated in original ADS with motionless flush-mounted receiver of flow. The functional scheme of aircraft’s air data system with motionless flush-mounted receiver of flow, built based on the original ion-mark sensor of aerodynamic angle and true airspeed, on receiving board of which the hole-receiver is installed to perceive

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Almeida, Arlan Scortegagna, and Vladimir Caramori Borges de Souza. "An alternative method for measuring velocities in open-channel flows: perfomance evaluation of a Pitot tube compared to an acoustic meter." RBRH 22 (March 13, 2017). http://dx.doi.org/10.1590/2318-0331.011716099.

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ABSTRACT Hydrometric measurements undertaken in channels with high velocities are conditioned to the particularities of the flow, which is often characterized by instantaneous fluctuations and disturbances on the free surface. In such cases, the uncertainties associated with velocity fluctuations exceed the precision offered by the instruments that are employed in conventional techniques. A reasonable accuracy of the results is therefore sufficient to accomplish the objective of the measurements. The use of devices based on Pitot’s principle in fast open-channel flows could be an effective alt

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Swischuk, Renee, and Douglas Allaire. "A Machine Learning Approach to Aircraft Sensor Error Detection and Correction." Journal of Computing and Information Science in Engineering 19, no. 4 (2019). http://dx.doi.org/10.1115/1.4043567.

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Sensors are crucial to modern mechanical systems. The location of these sensors can often make them vulnerable to outside interferences and failures, and the use of sensors over a lifetime can cause degradation and lead to failure. If a system has access to redundant sensor output, it can be trained to autonomously recognize errors in faulty sensors and learn to correct them. In this work, we develop a novel data-driven approach to detect sensor failures and predict the corrected sensor data using machine learning methods in an offline/online paradigm. Autocorrelation is shown to provide a glo

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Hyun Im, Ju, and Seung Jin Song. "Mixing and Entrainment Characteristics in Circular Short Ejectors." Journal of Fluids Engineering 137, no. 5 (2015). http://dx.doi.org/10.1115/1.4029412.

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Analytical and experimental investigations have been conducted to characterize the performance of “short” ejectors. In short ejectors, the core of primary (motive) flow still exists at the mixing duct exit, and nonuniform mixed flow is discharged from the mixing duct. Due to incomplete mixing, short ejector pumping performance is degraded and cannot be predicted by the existing “long” ejector models. The new analytical short ejector model presented in this paper is based on the control volume analysis and jet expansion model. The secondary (entrained) flow velocity and the corresponding shear

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Brachmanski, Roland, and Reinhard Niehuis. "Mach Number Distribution and Profile Losses for Low-Pressure Turbine Profiles With High Diffusion Factors." Journal of Turbomachinery 139, no. 10 (2017). http://dx.doi.org/10.1115/1.4036436.

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The results of this investigation come from two linear cascades at high diffusion factors (DFs). The measurements presented for each low-pressure turbine (LPT) profile were conducted at midspan under a range of Reynolds- and exit Mach numbers. The exit Mach number was varied in a range covering low subsonic up to values where a transonic flow regime on the suction side of the blade could be expected. This work focuses on two profiles with a diffusion factor in a range of 0.18≤DF≤0.22, where values in this range are considered as a comparable for the two cascades. Profile A is a front-loaded de

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"Fabrication and Experimentation of Diffuser Augmented Wind Turbine." International Journal of Recent Technology and Engineering 8, no. 2 (2019): 6047–52. http://dx.doi.org/10.35940/ijrte.b3792.078219.

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Wind Energy is turning into a big supply of renewable energy throughout the globe. This ever increasing field can probably reach the limit of accessibility and utility with the wind energy facility sites and size of the turbine itself. Therefore, it's needed to develop wind capturing devices that may produce energy within the locations wherever typical horizontal axis wind turbines (HAWTs) are too unrealistic to put in and operate. A diffuser augmented wind turbine (DAWT) is one such invention. DAWTs increase the ability output of the rotor by increasing the wind speed into the rotor employing

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Ubald, Bryn N., Rob Watson, Jiahuan Cui, Paul Tucker, and Shahrokh Shahpar. "Application of an Immersed Boundary Method on an Instrumented Turbine Blade With Large Eddy Simulation." Journal of Turbomachinery 143, no. 11 (2021). http://dx.doi.org/10.1115/1.4051110.

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Abstract Leading edge instrumentation used in compressor and turbine blades for jet-engine test rigs can cause significant obstruction and lead to a marked increase in downstream pressure loss. Typical instrumentation used in such a scenario could be a Kiel-shrouded probe with either a thermocouple or pitot-static tube for temperature/pressure measurement. High fidelity analysis of a coupled blade and probe requires the generation of a high-quality mesh which can take a significant amount of an engineers time. The application of an immersed boundary method (IBM) and large eddy simulation (LES)

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