scholarly journals MATERIALS PERFORMANCE PREDICTION FROM IRRADIATION TEST DATA.

1972 ◽  
Author(s):  
H. Yoshikawa
Keyword(s):  
Test Data ◽  
Performance Prediction ◽  
Irradiation Test

Comparison of Wind Turbine Performance Prediction and Measurement

1982 ◽  
Vol 104 (2) ◽  
pp. 84-88 ◽  
Author(s):  
J. L. Tangler
Keyword(s):  
Test Data ◽  
Wind Turbines ◽  
Performance Prediction ◽  
State Of The Art ◽  
Correlation Study ◽  
Performance Models ◽  
Rocky Flats ◽  
Turbine Performance ◽  
Horizontal Axis Wind Turbines ◽  
Development Center

The purpose of this work was to evaluate the state-of-the-art of performance prediction for small horizontal-axis wind turbines. This effort was undertaken since few of the existing performance methods used to predict rotor power output have been validated with reliable test data. The program involved evaluating several existing performance models from four contractors by comparing their predictions for two wind turbines with actual test data. Test data were acquired by Rocky Flats Test and Development Center and furnished to the contractors after submission of their prediction reports. The results of the correlation study will help identify areas in which existing rotor performance models are inadequate and, where possible, the reasons for the models shortcomings. In addition, several problems associated with obtaining accurate test data will be discussed.

scholarly journals Trim Solutions of Multirotor Vehicles using a Fast Performance Prediction Method

2021 ◽  
Author(s):  
Julia D. Tsaltas
Keyword(s):  
Test Data ◽  
Performance Prediction ◽  
Prediction Method ◽  
Flight Test ◽  
Performance Comparison ◽  
Performance Model ◽  
Pitching Moment ◽  
Rotor Speed ◽  
Power Prediction ◽  
Steady Level

A fast multirotor performance prediction method is presented. The method uses an algorithm to determine the flight performance and trim solutions of multirotor vehicles in steady, level flight. The method considers parasitic drag, force trim, fuselage interference, rotor interference, moment trim, and power prediction. In order to validate the method, vehicle lift, drag, and pitching moment predictions are compared to experimental data from NASA Ames for the 3DR Solo, a commercially available vehicle. The performance comparison with wind tunnel data show similar lift, drag and pitching moment trends when using estimated rotor and vehicle geometries. In addition, the predicted rotor speeds, vehicle power, and vehicle pitch are compared to flight test data of the Aeryon SkyRanger. The lead and rear rotor speed results show that the application of moment trim into the performance model provides rotor speed estimates that reflect the differential rotor speeds the flight test. An orientation study is conducted to explore the effects of rotor and fuselage interference velocities on rotor performance and the performance differences of a four-rotor vehicle flying in diamond and square configurations. Finally, a mass offset study is presented to predict the changes in rotor speed distribution of a SkyRanger vehicle when a 100 g mass is added to the support arm, which simulates asymmetry in centre of gravity location. The predicted performance results show overlapping results with flight testing with and without the mass offset at airspeeds below 5 m/s. At higher airspeeds, the rotor speed predictions that are established by moment trim requirements reflect the rotor speed trends shown from flight test data.

Performance Simulation of a Dual-Direction Ship in Level Ice

2014 ◽  
Vol 58 (03) ◽  
pp. 168-181
Author(s):  
Xiang Tang ◽  
Kaj Riska ◽  
Torgeir Moan
Keyword(s):  
Test Data ◽  
Model Test ◽  
Performance Prediction ◽  
Numerical Procedure ◽  
Model Tests ◽  
Prediction Tool ◽  
Continuous Mode ◽  
Performance Simulation ◽  
Level Ice ◽  
A Performance

The ice performance of a dual-direction ship is investigated through a numerical procedure developed to simulate the continuous-mode icebreaking in level ice. The effect of the propeller-hull-ice interaction for running astern is accounted for by applying the knowledge obtained from model tests to the numerical procedure. The numerical procedure is in turn used as a performance prediction tool to supplement the model test data to investigate the thrust deduction in ice.

Development, Testing, and Performance Prediction of Radial Compressor Stages for Multistage Industrial Compressors

1988 ◽  
Vol 110 (3) ◽  
pp. 283-292 ◽  
Author(s):  
P. Dalbert ◽  
M. V. Casey ◽  
E. Schurter
Keyword(s):  
Test Data ◽  
Performance Prediction ◽  
Simple Structure ◽  
Secondary Effects ◽  
Performance Measurements ◽  
Small Deviations ◽  
Radial Compressor ◽  
Multistage Compressors ◽  
Component Matching ◽  
And Performance

A review of some theoretical and experimental techniques currently in use for the aerodynamic development of standard stages for industrial centrifugal compressors is presented. Design methods for standardized families of radial compressor stages are summarized. The closed-loop test stands used for performance measurements are described and methods of test data analysis for identifying component performance and improving component matching are discussed. Test data obtained from standardized families of stages are analyzed using elementary dimensional analysis. This allows a simple structure for the interpolation of the large amounts of test data to be formulated. Correction formulae for secondary effects (such as changes in gas properties, Reynolds number, and small deviations from geometric similarity) are also derived from measurements. The data are incorporated into a stage-stacking calculation method for performance prediction of multistage compressors.

scholarly journals Trim Solutions of Multirotor Vehicles using a Fast Performance Prediction Method

2021 ◽  
Author(s):  
Julia D. Tsaltas
Keyword(s):  
Test Data ◽  
Performance Prediction ◽  
Prediction Method ◽  
Flight Test ◽  
Performance Comparison ◽  
Performance Model ◽  
Pitching Moment ◽  
Rotor Speed ◽  
Power Prediction ◽  
Steady Level

A fast multirotor performance prediction method is presented. The method uses an algorithm to determine the flight performance and trim solutions of multirotor vehicles in steady, level flight. The method considers parasitic drag, force trim, fuselage interference, rotor interference, moment trim, and power prediction. In order to validate the method, vehicle lift, drag, and pitching moment predictions are compared to experimental data from NASA Ames for the 3DR Solo, a commercially available vehicle. The performance comparison with wind tunnel data show similar lift, drag and pitching moment trends when using estimated rotor and vehicle geometries. In addition, the predicted rotor speeds, vehicle power, and vehicle pitch are compared to flight test data of the Aeryon SkyRanger. The lead and rear rotor speed results show that the application of moment trim into the performance model provides rotor speed estimates that reflect the differential rotor speeds the flight test. An orientation study is conducted to explore the effects of rotor and fuselage interference velocities on rotor performance and the performance differences of a four-rotor vehicle flying in diamond and square configurations. Finally, a mass offset study is presented to predict the changes in rotor speed distribution of a SkyRanger vehicle when a 100 g mass is added to the support arm, which simulates asymmetry in centre of gravity location. The predicted performance results show overlapping results with flight testing with and without the mass offset at airspeeds below 5 m/s. At higher airspeeds, the rotor speed predictions that are established by moment trim requirements reflect the rotor speed trends shown from flight test data.

Meanline Performance Prediction of Volutes in Centrifugal Compressors

1986 ◽  
Author(s):  
C. R. Weber ◽  
M. E. Koronowski
Keyword(s):  
Test Data ◽  
Performance Prediction ◽  
Tangential Velocity ◽  
Computer Programs ◽  
Head Loss ◽  
Slight Improvement ◽  
Centrifugal Compressors ◽  
New Models ◽  
Loss Models

Sources of head loss in compressor volutes are reviewed and new models for tangential velocity dump loss and for exit cone loss are presented for use in meanline performance prediction computer programs. The concept of equivalent sizing parameter, SP, for volutes is also introduced and is shown to be valuable for comparing tangential velocity dump loss models against test data. For SP ≥ 1 the new models for tangential velocity dump loss and exit cone loss show only a slight improvement over old loss models, but for SP<1 the new models are clearly superior.

Sign in / Sign up

Export Citation Format

Share Document