Calibration of the NASA GRC 16″ Mass-Flow Plug

Davis, David O.; Friedlander, David J.; Saunders, John D.; Frate, Franco C.; Foster, Lancert E.

doi:10.1115/fedsm2012-72266

Cited by 4 publications

(4 citation statements)

References 6 publications

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“…The mass flow control system relies on a plug nozzle that chokes a subsonic diffuser located downstream the exit of the intake duct and determines the operating condition, characterized by the Mach number at the AIP. The initial design of the plug nozzle system follows the design guidelines provided by Sasson [17] and Davis et al [18]. The mass flow control unit interface with the core exhaust system and silencers further downstream.…”

Section: Intake Rig Overall Plant Architecturementioning

confidence: 99%

Design of a high-speed intake distortion simulator for propulsion integration research

Migliorini

Szymański

Zachos

et al. 2023

AIAA SCITECH 2023 Forum

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High levels of inlet flow distortion can be a critical aspect in supersonic air induction systems due to the complex spatial nature and notable temporal unsteadiness. This can affect the operability and performance of the propulsion system. Simulation of the intake shock system in a relatively less expensive, lower technology readiness level experimental facility can be an important element to mitigate a significant part of the risk that industrial and certification testing carries. The work described in this paper is part of a programme that aims to develop such a distortion simulation test rig where the capability of advanced nonintrusive measurement techniques would be applied in propulsion integration research. The paper describes the concept, preliminary design and sizing of the working section of the rig, the exhaust system design and the integration of the test model. A brief summary of the rig architecture is provided along with details of the high-pressure system that drives the supersonic flow. The work indicates that careful design of the working section is required to ensure sufficient operating range and representative aerodynamics of the test model. It is also shown that the working section wall interference on the test model is tightly linked with the type and size of the aircraft intake to be tested. Ways to mitigate this interference are herein explored. I.Nomenclature ACIntake capture area AH Working section cross-sectional area A0 Area of stream tube entering the inlet Amax Maximum inlet projected area, A* Nozzle throat area Cp Static pressure coefficient H Working section height Ht Intake throat height h Diverter height

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Section: Intake Rig Overall Plant Architecturementioning

confidence: 99%

Design of a high-speed intake distortion simulator for propulsion integration research

Migliorini

Szymański

Zachos

et al. 2023

AIAA SCITECH 2023 Forum

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“…The mass-flow through the facility was measured with the ASME bellmouth by the method described in Ref. [10]. The mass-flow as a function C-D nozzle Reynolds number is shown in Figure 16.…”

Section: Asme Bellmouth and C-d Nozzle Conditionmentioning

confidence: 99%

CFD Validation Experiment of a Mach 2.5 Axisymmetric Shock-Wave/Boundary-Layer Interaction

Davis

2015

Volume 1: Symposia

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Preliminary results of an experimental investigation of a Mach 2.5 two-dimensional axisymmetric shock-wave/boundary-layer interaction (SWBLI) are presented. The purpose of the investigation is to create a SWBLI dataset specifically for CFD validation purposes. Presented herein are the details of the facility and preliminary measurements characterizing the facility and interaction region. These results will serve to define the region of interest where more detailed mean and turbulence measurements will be made.

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“…Accurate measurement of the mass flow rate is therefore necessary. Due to its mechanical simplicity, the air flow through an inlet is often controlled and measured with a Mass Flow Plug (MFP) which is typically a pipe whose exit area is regulated by translating a body of revolution along the axis of the pipe 1 . The body of revolution is usually conical, but other shapes have been used, and the pipe may either be constant area with a sharp corner or variable area with a contour at the exit.…”

Section: Introductionmentioning

confidence: 99%

Numerical Calibration of Mass Flow Plug for Inlet Testing

Sasson¹,

Davis²,

Barnhart³

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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A simple control volume model has been developed to calculate the discharge coefficient through a mass flow plug (MFP) and validated with a calibration experiment. The maximum error of the model within the operating region of the MFP is 0.54%. The control volume analysis developed work is comprised of a sequence of flow calculations through the MFP. The model uses the MFP geometry and operating pressure and temperature to couple continuity, momentum, energy, an equation of state, and wall shear. The discharge coefficient calculation also includes the effects of boundary layer growth, including the reduction in cross-sectional flow area as characterized by the boundary layer displacement thickness. The last calculation in the sequence uses an integral method to calculate the growth of the boundary layer, from which the displacement thickness is then determined. The result of these successive calculations is an accurate one-dimension model of the velocity, pressure, and temperature through the MFP. For comparison, a computational fluid dynamic (CFD) calibration is shown, which when compared to the presented numerical model, had a lower accuracy with a maximum error of 1.35% in addition to being slower by a factor of 100."

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Calibration of the NASA GRC 16″ Mass-Flow Plug

Cited by 4 publications

References 6 publications

Design of a high-speed intake distortion simulator for propulsion integration research

Design of a high-speed intake distortion simulator for propulsion integration research

CFD Validation Experiment of a Mach 2.5 Axisymmetric Shock-Wave/Boundary-Layer Interaction

Numerical Calibration of Mass Flow Plug for Inlet Testing

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