New Methodology for Wind Tunnel Calibration Using Neural Networks - EGD Approach

Mosbah, Abdallah Ben; Salinas, Manuel Flores; Botez, Ruxandra Mihaela; Dao, Thiên-My

doi:10.4271/2013-01-2285

Cited by 28 publications

(12 citation statements)

References 4 publications

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“…The LARCASE laboratory is equipped with the Price-Païdoussis subsonic wind tunnel ( Figure 12), which has already been used in many LARCASE projects [19,25,[28][29][30]).…”

Section: The Price-païdoussis Wind Tunnelmentioning

confidence: 99%

Design and Validation of a New Morphing Camber System by Testing in the Price—Païdoussis Subsonic Wind Tunnel

Communier¹,

Botez²,

Wong³

2020

Aerospace

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This paper presents the design and wind tunnel testing of a morphing camber system and an estimation of performances on an unmanned aerial vehicle. The morphing camber system is a combination of two subsystems: the morphing trailing edge and the morphing leading edge. Results of the present study show that the aerodynamics effects of the two subsystems are combined, without interfering with each other on the wing. The morphing camber system acts only on the lift coefficient at a 0° angle of attack when morphing the trailing edge, and only on the stall angle when morphing the leading edge. The behavior of the aerodynamics performances from the MTE and the MLE should allow individual control of the morphing camber trailing and leading edges. The estimation of the performances of the morphing camber on an unmanned aerial vehicle indicates that the morphing of the camber allows a drag reduction. This result is due to the smaller angle of attack needed for an unmanned aerial vehicle equipped with the morphing camber system than an unmanned aerial vehicle equipped with classical aileron. In the case study, the morphing camber system was found to allow a reduction of the drag when the lift coefficient was higher than 0.48.

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“…The LARCASE laboratory is equipped with the Price-Païdoussis subsonic wind tunnel ( Figure 12), which has already been used in many LARCASE projects [19,25,[28][29][30]).…”

Section: The Price-païdoussis Wind Tunnelmentioning

confidence: 99%

Design and Validation of a New Morphing Camber System by Testing in the Price—Païdoussis Subsonic Wind Tunnel

Communier¹,

Botez²,

Wong³

2020

Aerospace

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“…The measurements presented in this section were made during wind tunnel testing at a speed of 20 m/s and at an air density of 1.18 kg/m³. A more detailed description of the wind tunnel and its method of calibration can be found in [21]. centrifugal fan, a diffuser and settling chamber, a contraction section, and a working section.…”

Section: Experimental Setup Of the Mle Systemmentioning

confidence: 99%

“…The measurements presented in this section were made during wind tunnel testing at a speed of 20 m/s and at an air density of 1.18 kg/m³. A more detailed description of the wind tunnel and its method of calibration can be found in [21]. The aerodynamic loading scales installed in the wind tunnel measured the forces and moments experienced by the objects studied in the test section [22].…”

Section: Experimental Setup Of the Mle Systemmentioning

confidence: 99%

Design, Manufacturing, and Testing of a New Concept for a Morphing Leading Edge using a Subsonic Blow Down Wind Tunnel

Communier¹,

Besnerais²,

Botez³

et al. 2019

Biomimetics

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This paper presents the design and wind tunnel test results of a wing including a morphing leading edge for a medium unmanned aerial vehicle with a maximum wingspan of 5 m. The design of the morphing leading edge system is part of research on the design of a morphing camber system. The concept presented here has the advantage of being simple to manufacture (wooden construction) and light for the structure of the wing (compliance mechanism). The morphing leading edge prototype demonstrates the possibility of modifying the stall angle of the wing. In addition, the modification of the stall angle is performed without affecting the slope of the lift coefficient. This prototype is designed to validate the functionality of the deformation method applied to the leading edge of the wing. The mechanism can be further optimized in terms of shape and material to obtain a greater deformation of the leading edge, and, thus, to have a higher impact on the increase of the stall angle than the first prototype of the morphing leading edge presented in this paper.

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“…The goal was to reduce the drag by moving the transition location towards the trailing edge. The wind tunnel in which the experimental tests were conducted was calibrated by Mosbah et al 27 The pressure coefficients predicted numerically by Koreanschi et al 28 were compared with the pressure coefficients measured in the new calibrated wind tunnel.…”

Section: Introductionmentioning

confidence: 99%

A wind tunnel tested control system for a morphing wing actuation mechanism

Kammegne

Botez

Grigorie

et al. 2016

AIAA Atmospheric Flight Mechanics Conference

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The technique of morphing takes its origin from the bird flight and allows an airplane to change its original configuration during flight depending on the flight conditions. The main objective of the morphing is to improve the mission performance in order to optimize and control the fuel consumption efficiency. The experimental results of a morphing wing concept are presented on a part of the upper surface of the wing which is flexible. The wing was equipped with an aileron which was considered as a separated wing's entity. The objective was to reduce the drag by delaying or by moving the transition point towards the trailing edge. Another project objective was to compare the aerodynamics effects of the rigid aileron with the aerodynamic effects of the morphing aileron. The shape of the wing upper surface was modified by a set of four miniature electrical actuators inserted directly inside the wing. The positions of the actuators were controlled by four different controllers. These controllers have been designed based on the actuators simulation models. Three sets of wind tunnel tests have been performed with the manufactured demonstrator. Experimental resultsrevealed a promising controller behavior. The visualization of the flow over the wing upper surface was done with the infrared measurement technique. Using the same technique, the transition region location was estimated and compared with transition location determined by the pressure sensors array installed in the wing upper surface. Nomenclature M = Mach number α = Angle of attack β = Deflection angle CRIAQ = Consortium for Research and Innovation in Aerospace in Quebec LVDT = Linear Variable Differential Transducer

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New Methodology for Wind Tunnel Calibration Using Neural Networks - EGD Approach

Cited by 28 publications

References 4 publications

Design and Validation of a New Morphing Camber System by Testing in the Price—Païdoussis Subsonic Wind Tunnel

Design and Validation of a New Morphing Camber System by Testing in the Price—Païdoussis Subsonic Wind Tunnel

Design, Manufacturing, and Testing of a New Concept for a Morphing Leading Edge using a Subsonic Blow Down Wind Tunnel

A wind tunnel tested control system for a morphing wing actuation mechanism

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