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Author: Mark D'imperio Publisher: ISBN: Category : Languages : en Pages :
Book Description
A five-hole probe is a unique measuring device that can provide information on a flow field's three dimensional velocity vector. Many laboratories studying turbomachinery can utilize these probes to gather important information on complex flows that CFD software cannot always provide accurately. However, these probes can be difficult to calibrate and many laboratories do not have the capability of running their own calibrations. Often, they have to rely on the manufacturer's original calibration which can become inaccurate over time. This thesis presents the construction and validation of a five-hole probe calibration system.The calibration system designed in this research produces an air-jet in which the velocity and pressure can be measured by pressure taps built into the sides of the rig's piping. The system involves a series of pipes with a section of packed straws and three screens to reduce turbulence and straighten the flow in the system. To handle the probe's position and orientation, a traverse and rotary table system was built to control the probe both manually and through automation. The probe can then be orientated at various pitch and yaw angles to gather calibration data in the air-jet.This thesis demonstrates calibration runs for the intended use of the probe at Re[almost equal to]4842. After running repeated tests it was determined that the probe could produce reliable data for ranges of ±10o at this Reynold's number. Having the system in the lab also gives the ability to recalibrate the probe for other values for Re which may have other ranges of useable data.
Author: Mark D'imperio Publisher: ISBN: Category : Languages : en Pages :
Book Description
A five-hole probe is a unique measuring device that can provide information on a flow field's three dimensional velocity vector. Many laboratories studying turbomachinery can utilize these probes to gather important information on complex flows that CFD software cannot always provide accurately. However, these probes can be difficult to calibrate and many laboratories do not have the capability of running their own calibrations. Often, they have to rely on the manufacturer's original calibration which can become inaccurate over time. This thesis presents the construction and validation of a five-hole probe calibration system.The calibration system designed in this research produces an air-jet in which the velocity and pressure can be measured by pressure taps built into the sides of the rig's piping. The system involves a series of pipes with a section of packed straws and three screens to reduce turbulence and straighten the flow in the system. To handle the probe's position and orientation, a traverse and rotary table system was built to control the probe both manually and through automation. The probe can then be orientated at various pitch and yaw angles to gather calibration data in the air-jet.This thesis demonstrates calibration runs for the intended use of the probe at Re[almost equal to]4842. After running repeated tests it was determined that the probe could produce reliable data for ranges of ±10o at this Reynold's number. Having the system in the lab also gives the ability to recalibrate the probe for other values for Re which may have other ranges of useable data.
Author: Joint Institute for Aeronautics and Acoustics. Joint Institute for Aeronautics and Acoustics Publisher: ISBN: Category : Languages : en Pages : 88
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781725003941 Category : Languages : en Pages : 36
Book Description
A new algorithm for five-hole probe calibration and data reduction using a non-nulling method is developed. The significant features of the algorithm are: (1) two components of the unit vector in the flow direction replace pitch and yaw angles as flow direction variables; and (2) symmetry rules are developed that greatly simplify Taylor's series representations of the calibration data. In data reduction, four pressure coefficients allow total pressure, static pressure, and flow direction to be calculated directly. The new algorithm's simplicity permits an analytical treatment of the propagation of uncertainty in five-hole probe measurement. The objectives of the uncertainty analysis are to quantify uncertainty of five-hole results (e.g., total pressure, static pressure, and flow direction) and determine the dependence of the result uncertainty on the uncertainty of all underlying experimental and calibration measurands. This study outlines a general procedure that other researchers may use to determine five-hole probe result uncertainty and provides guidance to improve measurement technique. The new algorithm is applied to calibrate and reduce data from a rake of five-hole probes. Here, ten individual probes are mounted on a single probe shaft and used simultaneously. Use of this probe is made practical by the simplicity afforded by this algorithm. Reichert, Bruce A. and Wendt, Bruce J. Glenn Research Center NASA-TM-106458, E-8319, NAS 1.15:106458 RTOP 505-62-52...
Author: Brock Joseph Anthony Pleiman Publisher: ISBN: Category : Languages : en Pages : 150
Book Description
In airframe propulsion integration, the pressure recovered at the beginning of the inlet in comparison to the end of the inlet is a critical design point. Studies conducted by the Air Force Research Lab show that a loss in recovery pressure directly and adversely relates to the change in range of the aircraft. For that reason, accuracy of pressure instrumentation at the aerodynamic interface plane, or the interface between the end of the inlet and the beginning of the engine, is critical. Historically, data from experimental tests at the aerodynamic interface plane have mostly been reduced into time-averaged and time-independent pressures; however, current engine manufacturers are increasing focus on the angularity of the flow entering the engine. Currently airframe propulsion integration test programs require multiple runs to test each configuration with different sensor types to measure the time-dependent and time-independent pressure values, as well as, the angularity of the flow. Testing the same configuration multiple times can quickly become expensive in larger, production tunnels so a new probe design capable of capturing the time-independent and time-dependent pressures, in conjunction with the angularity of the flow has been designed.In order to determine whether the design of the probe is adequate for capturing all three variables similar to historical results shown by Paul[1], Kulite[2] and Arrend[3], a calibration must first be completed followed by the collection of additional data points which provide calibration validation. In order to calibrate the new probe, previously calibrated instrumentation will be used as a 0́−truth0́+ model. To ensure that the measurement uncertainty due to test set-up is comparable, the technique and test approach will be modeled after the calibration of a series of 5-hole probes calibrated at Wright Patterson Air Force Base.This thesis will document the experimental set-up, test approach, data acquired, data reduction and measurement uncertainty for a series of Mach numbers to determine if a 5-hole probe with a time-dependent pressure sensor in the center port is capable of accurately measuring steady state total and static pressure, Mach number, angle of attack and yaw, and dynamic content simultaneously.After running the calibration, it was found that the steady-state total and static pressure, angle of attack and yaw uncertainty are similar to the results previously published by Gallington[4], Paul[1] and Semmelmayer[5] if the Mach number is greater than Mach 0.2. The amplitude of nearly all of the frequencies detected in the experiment increased with angle of attack, angle of yaw and Mach number therefore leading to an increased RMS about the average reading of the sensor; however, a relationship between the RMS and angle of attack, angle of yaw and Mach number was found. This relationship showed that calibrating the RMS of the probe at an angle of attack to what the RMS of the flow would have been if the probe were axially aligned may be possible. Although the initial results of the RMS relationship are promising, the final results lack closure and require additional testing. In conclusion the probe is capable of accurately measuring total and static pressure, Mach, angle of attack and yaw while the axially aligned fluctuations require more research to validate the proposed equation.
Author: Mark D'imperio
Author: Mark D'imperio
Author: P. G. Smith
Author: Vijay Jadhav
Author: Joint Institute for Aeronautics and Acoustics. Joint Institute for Aeronautics and Acoustics
Author: National Aeronautics and Space Administration (NASA)
Author: Bruce A. Reichert
Author: Brock Joseph Anthony Pleiman
Author: Gregory G. Zilliac
Author: A.L. Treaster
Author: Scott O. Kjelgaard