Manufacturing Process of Blended Delta-Shaped Wing Model

2013 ◽  
Vol 845 ◽  
pp. 971-974 ◽  
Author(s):  
Shabudin Mat ◽  
I. Shah Ishak ◽  
Khidzir Zakaria ◽  
Z. Ajis Khan
Keyword(s):  
Wind Tunnel ◽  
Manufacturing Process ◽  
Delta Wing ◽  
Wind Tunnel Test ◽  
Aircraft Design ◽  
Wing Model ◽  
Tunnel Model ◽  
Cad Cam ◽  
Actual Flow ◽  
Flow Cycle

Aerodynamicists have long acknowledged the blended wing body (BWB) aircraft design could produce great aerodynamic advantages due to the integration of the delta wing structure with the thick center body. Therefore the wind tunnel test campaign is crucial to gain information of the flow field that governs the delta-shaped wing which has frequently baffled the aerodynamicists. In such, the wind tunnel test required acceptable quality of delta-shaped wing model for results validity. Consequently, the manufacturing process as well as the selection of the appropriate machinery tools, must be wisely designed and performed. The modular 3D concept in associating with CAD/CAM technology was utilised in the process. Finally, the actual flow cycle of manufactures blended BWB aircraft model was sucessfully established. The objective of this paper is to highlight those complexity manufacturing process and techniques involved in order to produce a good blended delta-shaped wind tunnel model.

An Historical and Applied Aerodynamic Study of the Wright Brothers’ Wind Tunnel Test Program and Application to Successful Manned Flight

2005 ◽  
Author(s):  
Michael G. Dodson ◽  
David S. Miklosovic
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Scaling Effects ◽  
Force Measurements ◽  
Velocity Gradients ◽  
Tunnel Model ◽  
Image Velocimetry ◽  
Manned Flight ◽  
Flow Quality ◽  
Scale Design

A replica wind tunnel was built and used to test the flow quality through the Wright Brothers’ wind tunnel. The research determined the effect flow quality and experimental method had on the Brothers’ results, and whether those results were useful in a quantitative sense. Particle image velocimetry revealed boundary layers extending 2.5” (63.5 mm) from each wall, and velocity gradients as large as 20% along the wind tunnel model span resulting in an asymmetric lift distribution. Similarly, the balance generated asymmetric wingtip vortices contributing to asymmetric downwash along the span of the model. Direct force measurements of a replica of the Wrights #12 airfoil showed their lift measurements were at least 7% and as much as 15% too low, and numerical analysis revealed wind tunnel predictions for lift, drag, and efficiency were not applicable to full scale design due to Reynolds number scaling effects.

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

Wind Tunnel Test of a Blended Wing Aircraft in Ground Effect With Active Flow Control

2016 ◽  
Author(s):  
Michael Mayo ◽  
Jonathan Carroll ◽  
Nicholas Motahari ◽  
Warren Lee ◽  
Robert Englar
Keyword(s):  
Wind Tunnel ◽  
Active Flow Control ◽  
Wind Tunnel Test ◽  
Ground Effect ◽  
Circulation Control ◽  
Wing Model ◽  
Subsonic Wind Tunnel ◽  
Test Methodology ◽  
Tunnel Floor ◽  
Lift And Drag

This paper describes the test methodology and results for a wind tunnel experiment featuring a blended wing aircraft in ground effect with built-in circulation control. A 82.55cm wingspan blended wing model was tested in a subsonic wind tunnel at velocities ranging from 18m/s – 49m/s and corresponding Reynolds numbers ranging from 130k – 350k. Pitch angle was held constant at 0 degrees and the height above the wind tunnel floor was modified to determine lift and drag modification due to ground effect. At a normalized height (y/bw) of 0.06, ground effect increased lift production by 24% and reduced drag by 22% when compared to a normalized height of 0.5. The addition of the circulation control significantly increased the lift production of the model at a cost of increased drag. At a normalized height of 0.031, the lift production increased by 200% at a blowing coefficient of 0.01, but the drag also increased by 72%, ultimately increasing L/D by 178%. Experimental results also suggest that ground effect and circulation control have a synergistic effect when used simultaneously. The effects of Reynolds number and circulation control slot height are also investigated.

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.

scholarly journals Desain dan Eksperimen Uji Getaran di Tanah dari Model Separuh Sayap Pesawat N219

WARTA ARDHIA ◽  
2017 ◽  
Vol 42 (3) ◽  
pp. 123
Author(s):  
Sayuti Syamsuar ◽  
Leonardo Gunawan ◽  
Martina Widiramdhani ◽  
Nina Kartika
Keyword(s):  
Wind Tunnel ◽  
Critical Phenomenon ◽  
Damping Ratio ◽  
Wind Tunnel Test ◽  
Ground Vibration ◽  
Parameter Analysis ◽  
Vibration Test ◽  
Software Analysis ◽  
Flutter Speed ◽  
Wing Model

Fenomena flutter merupakan salah satu fenomena yang kritis dan dapat membahayakan pesawat. Ketika, pesawat terbang semakin cepat dan mencapai kecepatan flutter, maka akan terjadi ketidakstabilan struktur. Oleh sebab itu, untuk menjamin keselamatan Pilot saat uji terbang, perlu dilakukan analisis awal pada kecepatan flutter. Uji terowongan angin selalu dilakukan untuk memvalidasi hasil dari analisis numerikal. Penelitian ini meliputi analisis program NASTRAN pada model separuh sayap pesawat N219 saat uji getaran di tanah. Prediksi kecepatan flutter secara analisis hampir sama dengan hasil uji terowongan angin. Parameter modus struktur yang ditemukan, seperti frekuensi natural, modus getar dan rasio redaman, dapat digunakan untuk analisis parameter flutter sebagai metoda analisis baru. [The Design and Experiment of Ground Vibration Test of N219 Aircraft Half Wing Model] Flutter phenomena is a critical phenomenon that can be dangerous for aircraft. When an aircraft fly faster until reach flutter speed, the structure will become unstable. Therefore, it is important to conduct preliminary analysis of flutter speed to ensure the safety of Pilot. Wind tunnel test is necessary to be conducted to validate numerical analysis results. This research consist of NASTRAN software analysis of half wing model of N219 aircraft for ground vibration test. The prediction of flutter speed which is obtained from software analysis is similar with the wind tunnel test result. It is found that the modus parameter of structure like natural frequency, modus of vibration and damping ratio can be used on the parameter analysis as a new analysis method.

scholarly journals Experimental and Computational Analysis of Model–Support Interference in Low-Speed Wind-Tunnel Testing of Fuselage-Boundary-Layer Ingestion

2019 ◽  
Vol 304 ◽  
pp. 02020
Author(s):  
Biagio Della Corte ◽  
André A.V. Perpignan ◽  
Martijn van Sluis ◽  
Arvind Gangoli Rao
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Wind Tunnel Test ◽  
Leading Edge ◽  
Horseshoe Vortex ◽  
Junction Flow ◽  
Tunnel Model ◽  
Aerodynamic Interaction ◽  
Support Interference ◽  
Model Support

Junction flow caused by the aerodynamic interaction between a wind-tunnel model and the support structure can largely influence the flowfield and hence the experimental results. This paper discusses a combined numerical and experimental study which was carried out to mitigate the model–support interference in a wind-tunnel test setup for the study of fuselage boundary-layer ingestion. The setup featured an axisymmetric fuselage mounted through a support beam, covered by a wing-shaped fairing. The junction flow appearing at the fuselage–fairing connection produced undesired flow distortions at the fuselage aft section, due to the formation of an horseshoe vortex structure at the fairing leading edge. Numerical and experimental analysis were performed with the aim of reducing the distortion intensity by improving the fairing design. Results show that modifying the leading-edge shape of the fairing effectively decreased the flowfield distortions. Moreover, the addition of a dummy fairing diametrically opposed to the first one was found to be beneficial due to the enhancement of the configuration symmetry.

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.

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.

Efficient stall compliance prediction method for trimmed very light aircraft with high-lift devices

2016 ◽  
Vol 231 (6) ◽  
pp. 1124-1137
Author(s):  
Nhu Van Nguyen ◽  
Daeyeon Lee ◽  
Maxim Tyan ◽  
Jae-Woo Lee ◽  
Sangho Kim
Keyword(s):  
Wind Tunnel ◽  
Stokes Equations ◽  
Transport Model ◽  
Three Dimensional ◽  
Wind Tunnel Test ◽  
Prediction Method ◽  
Aircraft Design ◽  
Design Stage ◽  
High Fidelity ◽  
Configuration Generation

An efficient stall compliance prediction method using quick configuration generation, adapted mesh, high fidelity analysis, and wind tunnel test data for trimmed very light aircraft is proposed. The three-dimensional Navier–Stokes equations are used to determine the characteristics of the flow field around the aircraft, and the [Formula: see text] shear stress transport model is used to interpret the turbulent flow as a solver in the high fidelity analysis. The calibrated mesh and model are developed by comparing the results with the wind tunnel test and adjusting the adapted mesh to match the wind tunnel data. The calibrated mesh and model are applied to conduct the full-scale very light aircraft analysis for the clean and full flap extended flight conditions to comply with the CS-VLA stall regulations. It is recommended that the flap area be increased in the trimmed full flap extended condition. The proposed method demonstrates the feasibility and effectiveness of very light aircraft VLA stall compliance prediction in reducing the development cost and time with small configuration changes at the preliminary very light aircraft design stage.

scholarly journals Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward-Swept Wing Model

2021 ◽  
Vol 2021 ◽  
pp. 1-12
Author(s):  
Yan Ouyang ◽  
Kaichun Zeng ◽  
Xiping Kou ◽  
Yingsong Gu ◽  
Zhichun Yang
Keyword(s):  
Wind Tunnel ◽  
Dynamic Pressure ◽  
Wind Tunnel Test ◽  
Swept Wing ◽  
Lattice Method ◽  
Model Calculations ◽  
Wind Tunnel Tests ◽  
Model Based ◽  
Wing Model ◽  
Fidelity Model

The static aeroelastic behaviours of a flat-plate forward-swept wing model in the vicinity of static divergence are investigated by numerical simulations and wind tunnel tests. A medium fidelity model based on the vortex lattice method (VLM) and nonlinear structural analysis is proposed to calculate the displacements of the wing structure with large deformation. Follower forces effect and geometric nonlinearity are considered to calculate the deformation of the wing by finite element method (FEM). In the wind tunnel tests, the divergence dynamic pressure is predicted by the Southwell method, and the static aeroelastic displacement is measured by a photogrammetric method. The results obtained by the medium fidelity model calculations show reasonable agreement with wind tunnel test results. A high fidelity model based on coupled computational fluid dynamics (CFD) and computational structural dynamics (CSD) predicts better results of the wing tip displacement when the freestream dynamic pressure is approaching the divergence dynamic pressure.

Sign in / Sign up

Export Citation Format

Share Document