Remote and Feedback Control of the Flap Angle in a Wind Tunnel Test Model by Optical Measurement

Chiba, Kazuhisa; Komatsu, Tatsuro; Kato, Hideaki; Nakakita, Kazuyuki

doi:10.3390/aerospace7020011

Cited by 5 publications

(3 citation statements)

References 17 publications

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“…The control system was constructed based on the optical measurement apparatus used in the previous study [5]. Note that the three apparatuses are modified for the current system.…”

Section: Optical Measurement For Feedback Controlmentioning

confidence: 99%

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Acquisition of Swept Aerodynamic Data by the Consecutive Changing of Wing Model Configuration in a Wind Tunnel Test Using Remote Feedback Control

et al. 2021

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This study conducted wind tunnel tests with consecutive deflection angle changes on a three-dimensional (3D) wing with a control surface to procure aerodynamic data by sweeping the deflection angle. Configuration changes of a wind tunnel test model, such as changing the deflection angle of control surfaces, are usually performed manually with the ventilation suspended. Hence, the number of configurations that can be implemented within a confined test period is restricted; the aerodynamic data gained are discrete values. To accomplish continuous angular modulation would dramatically improve the ability by sweeping through the aerodynamic data in wind tunnel tests, enhancing the test system as a tool for discussing complex physical phenomena. Thus, this study created a compact remote feedback control system using optical measurement to continuously obtain high-precision aerodynamic data without stopping the wind tunnel, eliminating human operation. In particular, this study targets a 3D wing wind tunnel model with a control surface, which is more challenging to fabricate, miniaturizing the system in a model. The system consequently attained consecutive aerodynamic data multiple times under numerous configurations, which had been impracticable to reach in the past, within a wind tunnel test period of several days, thereby dramatically increasing the testing capability. The reproducibility was quantitatively verified by comparing the multiple data for the identical configurations. Furthermore, the reliability was demonstrated using discrete data obtained by conventional stepwise deflection angle adjustments. Eventually, the system was able to grasp physical phenomena involving hysteresis.

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“…The control system was constructed based on the optical measurement apparatus used in the previous study [5]. Note that the three apparatuses are modified for the current system.…”

Section: Optical Measurement For Feedback Controlmentioning

confidence: 99%

“…A system has been developed previously, incorporating actuators inside the National Advisory Committee for Aeronautics (NACA) 0018 WTT model and deflecting the flap by remote control to solve this problem [5]. This system achieved the precise input deflection angle on the model by adding feedback control with optical measurement.…”

Section: Introductionmentioning

confidence: 99%

Acquisition of Swept Aerodynamic Data by the Consecutive Changing of Wing Model Configuration in a Wind Tunnel Test Using Remote Feedback Control

et al. 2021

Self Cite

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“…In the future, a comparison with wind tunnel test results is imperative to discuss aerodynamic performance errors on the C L -C D curve and to bring the robustness to the C L rise mechanism deduced by CFD. Thus, we are anticipating wind tunnel tests separately [3].…”

Section: Future Studiesmentioning

confidence: 99%

Aerodynamic efficacy of adding yaw-wise rotational degree of freedom to an airplane flap

Chiba

Komatsu

Ito

2020

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This study scrutinized the aerodynamic change of adding a yaw-wise rotational degree of freedom to a single slotted flap of airplane via computational fluid dynamic analyses. Existing slotted flaps have spanwise constant gaps and are disharmonious with the 3D nature of the flow field. A flap geometry and its angle condition are sensitive to aerodynamic performance; small variations in them must be useful in aerodynamic improvement. To add the yaw-wise rotation to a flap is a lower hurdle than to attain other high-lift systems. Therefore, after defining a simple configuration consisting of a fuselage, a wing, and a single slotted flap, we investigated the mesh dependency to consider the diversity in flow phenomena precisely; we examined the effect of the yaw-wise rotation for the flap on improving the whole lift. To place the flap at suitable yaw-wise rotation angles consequently effected raising the lift. We revealed the physical mechanism that accelerating the fluid in the gap between the wing and the flap changes the separation structure on the flap upper surface and grows the lift.

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A review of in-situ measurement and simulation technologies for ceramic sintering: towards a digital twin sintering system

Chen,

Ren,

Diao

et al. 2024

J Mater Sci

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Remote and Feedback Control of the Flap Angle in a Wind Tunnel Test Model by Optical Measurement

Cited by 5 publications

References 17 publications

Acquisition of Swept Aerodynamic Data by the Consecutive Changing of Wing Model Configuration in a Wind Tunnel Test Using Remote Feedback Control

Acquisition of Swept Aerodynamic Data by the Consecutive Changing of Wing Model Configuration in a Wind Tunnel Test Using Remote Feedback Control

Aerodynamic efficacy of adding yaw-wise rotational degree of freedom to an airplane flap

A review of in-situ measurement and simulation technologies for ceramic sintering: towards a digital twin sintering system

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