Supporting system interference on aerodynamic characteristics of an aircraft model in a low-speed wind tunnel

Ocokoljić, Goran; Rašuo, Boško; Kozić, Mirko

doi:10.1016/j.ast.2017.01.021

Cited by 56 publications

(29 citation statements)

References 10 publications

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“…Analysis of the measured aerodynamic coefficients from the point of symmetry was done for two Mach 0.25 runs of the ONERA M4 model in the modelupright and model-inverted positions [24] [25]. A good repeatability of the results of a model testing at φ = 0° and φ = 180° (Figure 24) is established, the deviations being attributed to the uncertainty of the internal balance used, which, because of the mechanical design of the model, had to be an assembled, Task-type one with accuracy somewhat lower than that of monolithic balances.…”

Section: Onera M4 Test Resultsmentioning

confidence: 99%

Contemporary frame of measurement and assessment of wind-tunnel flow quality in a low-speed facility

Ocokoljić¹,

Damljanović²,

Vuković³

et al. 2018

FME Transactions

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The requirements for the accuracy of measurements in a wind tunnel test become more and more severe while the complexity of the test increases. In an environment of reduced time available for wind tunnel test and increasing test costs, it is important that the accurate calibrations and verifications of all components of the measurement chain in a wind tunnel facility are established, maintained and statistically controlled through prolonged periods of time. The paper presents the efforts undertaken to establish and maintain a system of control of the quality of measurements in the T-35 4.4 m × 3.2 m low-speed wind tunnel of the Military Technical Institute in Belgrade. The assurance of the quality of measurement in this facility is based on ensuring the quality of three main constituents: the calibration of the test section of the wind tunnel, the calibration of the instrumentation used, and the periodic tests of the standard wind tunnel models. Sample results from relevant wind tunnel calibration tests are presented and compared with the results from other facilities. The tests confirmed a good overall quality of the facility, and that the achieved quality level has to be maintained, periodically checked and systematically documented.

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Section: Onera M4 Test Resultsmentioning

confidence: 99%

Contemporary frame of measurement and assessment of wind-tunnel flow quality in a low-speed facility

Ocokoljić¹,

Damljanović²,

Vuković³

et al. 2018

FME Transactions

Self Cite

View full text Add to dashboard Cite

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“…The traditional wind tunnel test include hard supporting fixtures [21,22], including abdominal support, tail support, back support [23], etc. With the development of mechanism technology, parallel support system and rope traction support system have emerged [24][25][26].…”

Section: Introductionmentioning

confidence: 99%

Full-Span Flying Wing Wind Tunnel Test: A Body Freedom Flutter Study

Shi

Liu

et al. 2020

Fluids

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Aiming at the experimental test of the body freedom flutter for modern high aspect ratio flexible flying wing, this paper conducts a body freedom flutter wind tunnel test on a full-span flying wing flutter model. The research content is summarized as follows: (1) The full-span finite element model and aeroelastic model of an unmanned aerial vehicle for body freedom flutter wind tunnel test are established, and the structural dynamics and flutter characteristics of this vehicle are obtained through theoretical analysis. (2) Based on the preliminary theoretical analysis results, the design and manufacturing of this vehicle are completed, and the structural dynamic characteristics of the vehicle are identified through ground vibration test. Finally, the theoretical analysis model is updated and the corresponding flutter characteristics are obtained. (3) A novel quasi-free flying suspension system capable of releasing pitch, plunge and yaw degrees of freedom is designed and implemented in the wind tunnel flutter test. The influence of the nose mass balance on the flutter results is explored. The study shows that: (1) The test vehicle can exhibit body freedom flutter at low airspeeds, and the obtained flutter speed and damping characteristics are favorable for conducting the body freedom flutter wind tunnel test. (2) The designed suspension system can effectively release the degrees of freedom of pitch, plunge, and yaw. The flutter speed measured in the wind tunnel test is 9.72 m/s, and the flutter frequency is 2.18 Hz, which agree well with the theoretical results (with flutter speed of 9.49 m/s and flutter frequency of 2.03 Hz). (3) With the increasing of the mass balance at the nose, critical speed of body freedom flutter rises up and the flutter frequency gradually decreases, which also agree well with corresponding theoretical results.

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“…In experiments, it is necessary to deeply consider tool factors, such as tool holders. Experimental results compared to CFDs will help in getting accurate results [33]. Zhang et al have investigated, numerically, the characteristics between the canard and wing of the canard-forward swept wing aircraft configurations at different canard [34].…”

Section: Introductionmentioning

confidence: 99%

Vortex Dynamics Study of the Canard Deflection Angles’ Influence on the Sukhoi Su-30-Like Model to Improve Stall Delays at High AoA

et al. 2019

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The maneuverability of the Sukhoi Su-30 at very high angles of attack (AoA) was remarkably appealing. Canard angle, in cooperation with aircraft wing, created a flow pattern whereby, in that position, the fighter still had as much lifting force as possible in order not to stall. The behavior of changing canard angle configuration played an essential role in creating the strong vortex core so that it could delay the stall. The study of vortex dynamics at canard deflection angle gave an essential function in revealing the stall delay phenomenon. In this study, one could analyze the flow patterns and vortex dynamics ability of the Sukhoi Su-30-like model to delay stall due to the influence of canard deflection. The used of water tunnel facilities and computational fluid dynamics (CFD) based on Q-criterion has obtained clear and detailed visualization and aerodynamics data in revealing the phenomenon of vortex dynamics. It was found that between 30° and 40° canard deflection configurations, Sukhoi Su-30-like was able to produce the most robust flow interaction from the canard to the main wing. It was clearly seen that the vortex merging formation above the fighter heads was clearly visible capable of delaying stall until AoA 80°.

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Supporting system interference on aerodynamic characteristics of an aircraft model in a low-speed wind tunnel

Cited by 56 publications

References 10 publications

Contemporary frame of measurement and assessment of wind-tunnel flow quality in a low-speed facility

Contemporary frame of measurement and assessment of wind-tunnel flow quality in a low-speed facility

Full-Span Flying Wing Wind Tunnel Test: A Body Freedom Flutter Study

Vortex Dynamics Study of the Canard Deflection Angles’ Influence on the Sukhoi Su-30-Like Model to Improve Stall Delays at High AoA

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