scholarly journals Design and Optimization of an Aeroservoelastic Wind Tunnel Model

Fluids ◽  
2020 ◽  
Vol 5 (1) ◽  
pp. 35 ◽  
Author(s):  
Johannes K. S. Dillinger ◽  
Yasser M. Meddaikar ◽  
Jannis Lübker ◽  
Manuel Pusch ◽  
Thiemo Kier
Keyword(s):  
Finite Element ◽  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Objective Functions ◽  
Dynamic Identification ◽  
Wind Tunnel Model ◽  
Design And Optimization ◽  
Aeroelastic Model ◽  
Tunnel Model ◽  
Gust Load Alleviation

Through the combination of passive and active load alleviation techniques, this paper presents the design, optimization, manufacturing, and update of a flexible composite wind tunnel model. In a first step, starting from the specification of an adequate wing and trailing edge flap geometry, passive, static aeroelastic stiffness optimizations for various objective functions have been performed. The second optimization step comprised a discretization of the continuous stiffness distributions, resulting in manufacturable stacking sequences. In order to determine which of the objective functions investigated in the passive structural optimization most efficiently complemented the projected active control schemes, the condensed modal finite element models were integrated in an aeroelastic model, involving a dedicated gust load alleviation controller. The most promising design was selected for manufacturing. The finite element representation could be updated to conform to the measured eigenfrequencies, based on the dynamic identification of the model. Eventually, a wind tunnel test campaign was conducted in November 2018 and results have been examined in separate reports.

J0501-3-4 Optimization of aerodynamic shape using deformable wind tunnel model for wind tunnel test

2009 ◽  
Vol 2009.7 (0) ◽  
pp. 29-30
Author(s):  
Futoshi NAGAMINE ◽  
Hiroaki KISHIGE ◽  
Mitsuru IKEDA ◽  
Takeshi MITSUMOJI ◽  
Masahiro SUZUKI
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Wind Tunnel Model ◽  
Aerodynamic Shape ◽  
Tunnel Model

Current Drag From Tow and Wind Tunnel Tests of a FLNG Hull

2016 ◽  
Author(s):  
Zhenjia (Jerry) Huang ◽  
Jang Kim ◽  
Hyunchul Jang ◽  
Scott T. Slocum
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Model Test ◽  
Cfd Simulation ◽  
Wind Tunnel Test ◽  
Model Tests ◽  
Additional Contribution ◽  
Wind Tunnel Model ◽  
Tunnel Model ◽  
Current Drag

In this paper, the current drag of a barge-shaped floating liquefied natural gas (FLNG) vessel was studied. Three model tests were performed — a wind tunnel model test, a submerged double-body tow test and a surface tow test. Computational fluid dynamics (CFD) simulations were carried out to gain further insights into the test results. During testing, the tow speed was kept low to avoid surface waves. When the current heading was around the beam current direction, the transverse drag coefficient measured from the wind tunnel test was significantly lower than those of the submerged tow and surface tow tests. The submerged tow and the surface tow provided similar drag coefficients. Results presented in this paper indicated that the difference between the wind tunnel test and the tow tests was caused by the wind tunnel boundary layer effect on the incoming wind profile and formation of a recirculation zone on the upstream side of the model, with a possible additional contribution from the wind tunnel floor constraint on the flow in the wake. Such effects are not accounted for with the simple corrections based on flow velocity reduction in the wind tunnel boundary layer. When conducting future wind tunnel model tests for barge-shaped FLNG hulls, one should consider the potential under-measurement of the transverse drag. In this paper, details of the FLNG model, test setup, test quality assurance (QA), measurement and CFD simulation results are presented, as well as discussions and recommendations for model testing.

Design and fabrication of an aircraft static aeroelastic model based on rapid prototyping

2015 ◽  
Vol 21 (1) ◽  
pp. 34-42 ◽  
Author(s):  
Chao Wang ◽  
Guofu Yin ◽  
Zhengyu Zhang ◽  
Shuiliang Wang ◽  
Tao Zhao ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Rapid Prototyping ◽  
Wind Tunnel Testing ◽  
Wind Tunnel Model ◽  
Content Type ◽  
Aeroelastic Model ◽  
Tunnel Model ◽  
Metal Frame ◽  
Stiffness Distribution ◽  
Tunnel Testing

Purpose – The purpose of this paper is to introduce a novel method for developing static aeroelastic models based on rapid prototyping for wind tunnel testing. Design/methodology/approach – A metal frame and resin covers are applied to a static aeroelastic wind tunnel model, which uses the difference of metal and resin to achieve desired stiffness distribution by the stiffness similarity principle. The metal frame is made by traditional machining, and resin covers are formed by stereolithgraphy. As demonstrated by wind tunnel testing and stiffness measurement, the novel method of design and fabrication of the static aeroelastic model based on stereolithgraphy is practical and feasible, and, compared with that of the traditional static elastic model, is prospective due to its lower costs and shorter period for its design and production, as well as avoiding additional stiffness caused by outer filler. Findings – This method for developing static aeroelastic wind tunnel model with a metal frame and resin covers is feasible, especially for aeroelastic wind tunnel models with complex external aerodynamic shape, which could be accurately constructed based on rapid prototypes in a shorter time with a much lower cost. The developed static aeroelastic aircraft model with a high aspect ratio shows its stiffness distribution in agreement with the design goals, and it is kept in a good condition through the wind tunnel testing at a Mach number ranging from 0.4 to 0.65. Research limitations/implications – The contact stiffness between the metal frame and resin covers is difficult to calculate accurately even by using finite element analysis; in addition, the manufacturing errors have some effects on the stiffness distribution of aeroelastic models, especially for small-size models. Originality/value – The design, fabrication and ground testing of aircraft static aeroelastic models presented here provide accurate stiffness and shape stimulation in a cheaper and sooner way compared with that of traditional aeroelastic models. The ground stiffness measurement uses the photogrammetry, which can provide quick, and precise, evaluation of the actual stiffness distribution of a static aeroelastic model. This study, therefore, expands the applications of rapid prototyping on wind tunnel model fabrication, especially for the practical static aeroelastic wind tunnel tests.

scholarly journals Aeroservoelastic Wind-Tunnel Test of the SUGAR Truss Braced Wing Wind-Tunnel Model

2015 ◽  
Author(s):  
Robert C. Scott ◽  
Timothy Allen ◽  
Mark Castelluccio ◽  
Bradley Sexton ◽  
Scott Claggett ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Wind Tunnel Model ◽  
Tunnel Model

scholarly journals Inter-Facility Correlations of Transonic Test Results of the AGARD-C Standard Wind-Tunnel Model

2018 ◽  
Vol 5 (13) ◽  
pp. 26476-26481
Author(s):  
Dijana Damljanović ◽  
Jovan Isaković ◽  
Marko Miloš
Keyword(s):  
Wind Tunnel ◽  
Test Results ◽  
Wind Tunnel Model ◽  
Tunnel Model

Evaluation of an I-box wind tunnel model for assessment of behavioral responses of blow flies

2013 ◽  
Vol 112 (11) ◽  
pp. 3789-3798 ◽  
Author(s):  
Kittikhun Moophayak ◽  
Kabkaew L. Sukontason ◽  
Hiromu Kurahashi ◽  
Roy C. Vogtsberger ◽  
Kom Sukontason
Keyword(s):  
Wind Tunnel ◽  
Behavioral Responses ◽  
Wind Tunnel Model ◽  
Blow Flies ◽  
Tunnel Model
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