High speed wind tunnel force test with traditional pressure-test-model

2020 ◽  
Vol 34 (14n16) ◽  
pp. 2040101
Author(s):  
Jichuan Su ◽  
Yong Huang ◽  
Shidong Zhong ◽  
Yujie Shi ◽  
Yonghong Li
Keyword(s):  
Wind Tunnel ◽  
High Speed ◽  
Low Cost ◽  
Aircraft Design ◽  
Test Model ◽  
Test Results ◽  
Pressure Tests ◽  
Pressure Test ◽  
Precision And Accuracy

Usually, force tests and pressure tests are conducted with different model in wind tunnel which could cause trouble for aircraft design as the pressure test results always could not match the force test results. So attempts to do force tests along with pressure tests are conducted. Results show that it is possible to do force test based on pressure-test-model when some improvements are done with the model and sting. Both force and pressure test results can be measured at the same time. The amount of pressure test results need not be reduced, and yet precision and accuracy of the force tests are acceptable for aircraft design, and this technology can be popularized with low cost.

Videogrammetric Techniques for Wind Tunnel Testing and Applications

2014 ◽  
Vol 986-987 ◽  
pp. 1629-1633
Author(s):  
Zheng Yu Zhang ◽  
Xu Hui Huang ◽  
Jiang Yin ◽  
Han Xuan Lai
Keyword(s):  
Wind Tunnel ◽  
Wave Front ◽  
High Speed ◽  
Marked Point ◽  
Wind Tunnel Test ◽  
Wind Tunnels ◽  
Test Model ◽  
Wind Tunnel Testing ◽  
Section Size ◽  
Key Techniques

Videogrammetric measurement is a research focus for the organizations of wind tunnel test because of its no special requirements on the test model, its key techniques for the vibration environment of the high speed wind tunnel are introduced by this paper, such as the solution of exterior parameters with big-angle large overlap, the algorithm of image processing for extracting marked point, the method of camera calibration and wave-front distortion field measurement. The great requirements and application prospects of videogrammetry in wind tunnel fine testing have been demonstrated by several practice experiments, including to measure test model’s angle of attack, dynamic deformations and wave-front distortion field in high speed wind tunnels whose test section size is 2 meters.

CFD Assessment of Rotordynamic Coefficients in Labyrinth Seals

2014 ◽  
Author(s):  
Sai S. Sreedharan ◽  
Giuseppe Vannini ◽  
Hiteshkumar Mistry
Keyword(s):  
High Speed ◽  
Test Results ◽  
Active Magnetic Bearings ◽  
Test Rig ◽  
Labyrinth Seals ◽  
Cfd Simulations ◽  
Flow Solver ◽  
Rotordynamic Coefficients ◽  
Pressure Test ◽  
Dynamic Seal

Seals used in high speed centrifugal compressors are prone to generate rotordynamic (RD) instabilities. To further understand their influence, a CFD based approach is developed. The objective of the current study is to numerically investigate and characterize the RD coefficients, representative of the dynamic seal forces. Experiments were carried out at high pressure test rig (up to 200 bar seal inlet pressure) which runs at 10000 RPM and has a high pre-swirl (about 0.9) along the same direction of rotor rotation. The rotor shaft in the experiment was instrumented with active magnetic bearings (AMBs) to linearly excite the rotor at three different frequencies: 28 Hz, 70 Hz and 126 Hz. Each frequency is characterized by amplitude of vibration and a phase. CFD simulations were carried out using commercial flow solver, using similar boundary conditions as that of experiments. The paper describes details of CFD model and its comparison against experiments. Numerical results show reasonable agreement of RD coefficients with test results. This job has to be considered as a first approach to CFD methodology applied to annular seals for the authors.

scholarly journals Geometric Effects Analysis and Verification of V-Shaped Support Interference on Blended Wing Body Aircraft

2020 ◽  
Vol 10 (5) ◽  
pp. 1596
Author(s):  
Xin Xu ◽  
Qiang Li ◽  
Dawei Liu ◽  
Keming Cheng ◽  
Dehua Chen
Keyword(s):  
Wind Tunnel ◽  
High Speed ◽  
Pitching Moment ◽  
Straight Section ◽  
Test Results ◽  
Wind Tunnel Tests ◽  
Blended Wing Body ◽  
Support Interference ◽  
Geometric Effects ◽  
Good Agreement

A special V-shaped support for blended wing body aircraft was designed and applied in high-speed wind tunnel tests. In order to reduce the support interference and explore the design criteria of the V-shaped support, interference characteristics and geometric parameter effects of V-shaped support on blended wing body aircraft were numerically studied. According to the numerical results, the corresponding dummy V-shaped supports were designed and manufactured, and verification tests was conducted in a 2.4 m × 2.4 m transonic wind tunnel. The test results were in good agreement with the numerical simulation. Results indicated that pitching moment of blended wing body aircraft is quite sensitive to the V-shaped support geometric parameters, and the influence of the inflection angle is the most serious. To minimize the pitching moment interference, the straight-section diameter and inflection angle should be increased while the straight-section length should be shortened. The results could be used to design special V-shaped support for blended wing body aircraft in wind tunnel tests, reduce support interference, and improve the accuracy of test results.

Design and Application of an all Moving Wing Model Limiting and Locking Device

2013 ◽  
Vol 753-755 ◽  
pp. 1031-1034 ◽  
Author(s):  
Bo Lu ◽  
Bin Bin Lv ◽  
Li Yu ◽  
Hong Tao Guo ◽  
Yu Yan ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Test Data ◽  
High Speed ◽  
Wind Tunnel Test ◽  
Test Equipment ◽  
Test Model ◽  
Wing Flutter ◽  
Wing Model ◽  
Control Principle ◽  
Design And Application

To effectively excite the all moving wing flutter model and limiting or quick locking model in case of bigger amplitude of the model, an excitation and limiting and locking device is designed for the high-speed wind tunnel flutter test model. This paper introduces the structure arrangement, control principle and strategy of this device. The wind tunnel flutter test indicates that this device can enhance the SNR of the test data, improve the boundary prediction precision of flutter, prevent the model from entering the flutter divergence state and protect the model and wind tunnel test equipment.

Movable Instantaneous Impact Pressure Testing Device

2009 ◽  
Author(s):  
Hongbiao Han ◽  
Jishun Li ◽  
Bing Wang ◽  
Dandan Liu ◽  
Yonggang Liu
Keyword(s):  
Power Supply ◽  
High Speed ◽  
Impact Pressure ◽  
Control Mode ◽  
Test Results ◽  
Adverse Conditions ◽  
Pressure Test ◽  
Mems Technology ◽  
Dsp Control ◽  
Design And Manufacture

A movable instantaneous impact pressure test device is designed and achieved, according to the characteristic of instantaneous impact wave such as acutely variation and large range of pressure, adverse conditions on the spot. A piezoresistive transducer of high-frequency an high pressure is selected and used. MEMS technology is adopted to design and manufacture the sensor that is flush packaged. In addition multi-channel analogue amplified circuit and DSP control core circuit are studied. So the multilevel multiple pressure analogue signals can be achieved. The circuit can take charge of high speed sampling, processing and storing of analogue signal too. Software modifying mode, process parameter and data transmission is also developed. The device has the function of scheduling of timing sample, automatic gain of magnification, automatic detection of the beginning of impact pressure, parameterization of working mode and process etc. It is a practical instrument with battery as power supply, the low power consumption of power supply control mode and the solid mental shell for testing explosion shock wave. Pressure test results indicated accurate pressure waves of instantaneous impact can be got with the instrument.

Comparison Between Pressure Tests and Simulations for Thickness Management of Wall Thinning T-Joints

2012 ◽  
Author(s):  
Kaina Teshima ◽  
Mayumi Ochi ◽  
Seiji Asada ◽  
Kiminobu Hojo ◽  
Takahiro Suzuki ◽  
...  
Keyword(s):  
Experimental Tests ◽  
Ultimate Tensile Stress ◽  
Fe Analysis ◽  
Test Results ◽  
Minimum Thickness ◽  
T Joints ◽  
Wall Thinning ◽  
Pressure Tests ◽  
Pressure Test ◽  
Design Pressure

Although the required minimum thickness (tsr) of T-joints (tees) is calculated from the design pressure and temperature for design, there are no rules or standards for thickness management of wall thinning T-joints for facilities maintenance. This paper describes the comparison between the five pressure test results of T-joints and their numerical simulations using FE analysis and confirms the failure criterion. The investigation for the numerical simulation and the experimental tests showed that ultimate tensile stress (σu) is the most suitable criterion for the burst of T-joints.

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