Supersonic Retropropulsion Computational Fluid Dynamics Validation with Langley 4×4 Foot Test Data

2014 ◽  
Vol 51 (3) ◽  
pp. 693-714 ◽  
Author(s):  
Daniel Guy Schauerhamer ◽  
Kerry A. Zarchi ◽  
William L. Kleb ◽  
Jan-Reneé Carlson ◽  
Karl. T. Edquist
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Test Data ◽  
Supersonic Retropropulsion

Supersonic Retropropulsion Computational-Fluid-Dynamics Validation with Ames 9×7 Foot Test Data

2014 ◽  
Vol 51 (3) ◽  
pp. 735-749 ◽  
Author(s):  
Daniel Guy Schauerhamer ◽  
Kerry A. Zarchi ◽  
William L. Kleb ◽  
Karl T. Edquist
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Test Data ◽  
Supersonic Retropropulsion

An Investigation of Air-Cooled Steam Condenser Performance Under Windy Conditions Using Computational Fluid Dynamics

2011 ◽  
Vol 133 (6) ◽  
Author(s):  
M. T. F. Owen ◽  
D. G. Kröger
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Performance Evaluation ◽  
Test Data ◽  
Reliable Method ◽  
Numerical Results ◽  
Pressure Jump ◽  
Fan Performance ◽  
Computational Fluid Dynamics Cfd ◽  
Full Scale Tests

The development of an efficient and reliable method of evaluating the performance of an air-cooled steam condenser (ACC) under windy conditions using computational fluid dynamics (CFD) is presented. A two-step modeling approach is employed as a result of computational limitations. The numerical ACC model developed in this study makes use of the pressure jump fan model, among other approximations, in an attempt to minimize the computational expense of the performance evaluation. The accuracy of the numerical model is verified through a comparison of the numerical results to test data collected during full-scale tests carried out on an operational ACC. Good correlation is achieved between the numerical results and test data. The effect of wind on ACC performance at El Dorado Power Plant (Nevada, USA) is investigated. It is found that reduced fan performance due to distorted flow at the inlet of the upstream fans is the primary contributor to the reduction in ACC performance associated with increased wind speed in this case. The model developed in this study has the potential to allow for the evaluation of large ACC installations and provides a reliable platform from which further investigations into improving ACC performance under windy conditions can be carried out.

Laboratory Formation Damage Test Data Upscaled With Computational Fluid Dynamics

2021 ◽  
Vol 73 (03) ◽  
pp. 63-64
Author(s):  
Judy Feder
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Steady State ◽  
Laboratory Test ◽  
Test Data ◽  
Test Fluid ◽  
Formation Damage ◽  
Cfd Simulations ◽  
Mud Cake ◽  
Completion Fluids

This article, written by JPT Technology Editor Judy Feder, contains highlights of paper SPE 199268, “Upscaling Laboratory Formation Damage Laboratory Test Data,” by Michael Byrne, SPE, Lesmana Djayapertapa, and Ken Watson, SPE, Lloyd’s Register, et al., prepared for the 2020 SPE International Conference and Exhibition on Formation Damage Control, Lafayette, Louisiana, 19-21 February. The paper has not been peer reviewed. Through several case histories, the complete paper demonstrates applications of computational fluid dynamics (CFD) modeling to upscaling of laboratory-measured formation damage and reveals implications for well and completion design. The value of laboratory testing is quantified and interesting challenges to conventional wisdom are highlighted. Introduction Laboratory formation damage testing is often used to help select optimal drilling and completion fluids. Test procedures such as sand retention and return permeability represent an attempt to simulate near-wellbore conditions during well construction and production. To determine what degree of permeability impairment is allowable, further interpretation that cannot be provided using classical nodal analysis or reservoir simulation methods is required. The complete paper describes the evolution of, and potential for, more-comprehensive upscaling and outlines the importance of consideration of full well geometry when designing and interpreting coreflood tests for formation damage. CFD simulations provide a means to upscale suitable laboratory test data to predict effect on well performance. Methods CFD simulations use a relatively simple, steady-state, static damage model that takes endpoint data from laboratory core tests and translates the data into parameters that are used for input into well geometry. Although this method has its merits and is a considerable advance on previous, more-simplistic upscaling attempts, it does not necessarily present the full picture of damage evolution in the near-wellbore. A transient model of damage with data again derived from laboratory coreflood data could reveal more about well cleanup and progressive damage removal. Steady-State Modeling. No API recommended practice for return permeability testing exists. Laboratories have their own procedures that comply broadly with recommended procedures developed some time ago. Operators and consultants, too, have their own procedures, which they often ask laboratories to follow. Although no recommended practice exists, evaluation of drilling and completion fluids usually involves measurement of a base permeability and remeasurement of a return permeability—or several—after application of the test fluid or fluids. In many cases, the laboratory removes the external mud cake or trims a slice of the end of the plug to measure return permeability without mud cake (Fig. 1).

Prediction of Warship Manoeuvring Coefficients using CFD

2015 ◽  
Author(s):  
C. Oldfield ◽  
M. Moradi Larmaei ◽  
A. Kendrick ◽  
K. McTaggart
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Physical Model ◽  
Test Data ◽  
Model Test ◽  
Verification And Validation ◽  
Planar Motion ◽  
Physical Model Test ◽  
Motion Mechanism ◽  
Planar Motion Mechanism

Verification and validation has been completed for the use of computational fluid dynamics as a practical means of simulating captive manoeuvring model tests. Verification includes spatial and temporal refinement studies. Direct validation includes the comparison of individual steady drift and planar motion mechanism simulations to physical model test data. Rotating arm simulations are validated indirectly on the basis of manoeuvring derivatives developed from the PMM tests. The merits of steady and unsteady simulations are discussed.

scholarly journals An investigation into contracted loaded tip propellers using computational fluid dynamics (CFD)

2018 ◽  
Author(s):  
N R J Williams
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Test Data ◽  
Experimental Test ◽  
Performance Improvements ◽  
Computational Fluid Dynamics Cfd ◽  
And Performance ◽  
Cfd Method ◽  
Developed Pressure

This paper investigates the potential performance improvements of adding contracted loaded tips to propellers. A Wageningen B5-75 Series propeller has been simulated and verified against published experimental test data. Contracted tips have then been added to a Wageningen propeller and the modified propeller then simulated. A CFD method and model has been developed. Pressure, velocity and vector plots have all been analysed detailing the mechanism behind the contracted tips. Limitations behind this method have been explored and explained, and recommendations for further studies made. The development of a database of propeller characteristics and performance chart data to allow quick evaluation of designs has also been proposed. 

Rotordynamic Characteristics Prediction for Hole-Pattern Seals Using Computational Fluid Dynamics

2020 ◽  
Vol 142 (2) ◽  
Author(s):  
Manish R. Thorat ◽  
James R. Hardin
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Test Data ◽  
Flow Model ◽  
Bulk Flow ◽  
Pitot Tube ◽  
Single Frequency ◽  
Test Case ◽  
Swirl Ratio ◽  
Rotordynamic Coefficients

Abstract The experimental setup for a hole-pattern seal is modeled using computational fluid dynamics (CFD) and results compared with measured test data and bulk flow model (ISOTSEAL) predictions. The inlet swirl boundary condition for prior CFD analyses of this test case have either been assumed or based on pitot-tube measurements. In this paper, the validity of each is investigated by including radial inlet nozzles with the inlet plenum in the model geometry. A transient mesh deformation technique with multiple frequency journal excitations is used to determine frequency-dependent rotordynamic coefficients. This multifrequency excitation method is validated against single frequency sinusoidal journal excitation. An empirical limit on the number of frequencies that can be packed in a multifrequency excitation signal to provide a reasonable estimate of rotordynamic coefficients is provided. Rotordynamic coefficients estimated using CFD compare well with measured rotordynamic coefficients. For the given test data, the ISOTSEAL bulk flow model does not provide good correlation for cross-coupled stiffness if the measured swirl ratio at the inlet of the seal is used in the prediction. However, improvement in correlation for cross-coupled stiffness is obtained if the swirl ratio found from CFD analysis is used in the bulk flow model, indicating that pitot-tube measurements of swirl may not be accurate.

scholarly journals Computational fluid dynamics trimming of helicopter rotor in forward flight

2020 ◽  
Vol 12 (5) ◽  
pp. 168781402092525 ◽  
Author(s):  
Chenglong Zhou ◽  
Ming Chen
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Test Data ◽  
Pitch Angle ◽  
Flight Test ◽  
Helicopter Rotor ◽  
Main Rotor ◽  
Forward Flight ◽  
Thrust Coefficient ◽  
Moment Coefficient

A computational fluid dynamics (CFD) trimming method based on wind tunnel and flight test data is proposed. Aerodynamic coefficients obtained for a helicopter rotor using this method were compared with both experimental data from a test report and CFD results based on the control parameters that were reported in the same document. The method applies small disturbances to the collective pitch angle, the lateral cyclic pitch angle and the longitudinal cyclic pitch angle of the helicopter’s main rotor during forward flight to analyze the effects of each disturbance on the thrust coefficient, the pitching moment coefficient and the rolling moment coefficient of the rotor. Then, by solving a system of linear equations, the collective pitch angle, the lateral cyclic pitch angle and the longitudinal cyclic pitch angle of the main rotor in the CFD trim state are obtained. The AH-1G rotor is used in this paper. NASA has conducted a comprehensive flight test program on this model and has published detailed test reports. Using this method, the pitch moment and the roll moment can be corrected to almost zero and the calculated thrust coefficient is more consistent with the test data when compared with results from direct CFD simulations.

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