Rapid Prototyping as a Tool to Support Wind Tunnel Testing of Unconventional Unmanned Airships

2013 ◽  
Author(s):  
Alessandro Ceruti ◽  
Piergiovanni Marzocca ◽  
Casey Stockbridge
Keyword(s):  
Wind Tunnel ◽  
Rapid Prototyping ◽  
Wind Tunnel Testing ◽  
Tunnel Testing

scholarly journals Application of Rapid Prototyping Technologies to Wind Tunnel Testing of High-Performance Vehicles

2019 ◽  
Author(s):  
Bruno Ricardo Massucatto Padilha ◽  
Guilherme Barufaldi ◽  
Roberto Gil Annes da Silva ◽  
César Augusto Duarte Rodrigues
Keyword(s):  
Wind Tunnel ◽  
Rapid Prototyping ◽  
High Performance ◽  
Wind Tunnel Testing ◽  
Tunnel Testing

Application of rapid prototyping models to transonic wind tunnel testing

1997 ◽  
Author(s):  
A. Springer ◽  
K. Cooper ◽  
F. Roberts ◽  
A. Springer ◽  
K. Cooper ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Rapid Prototyping ◽  
Wind Tunnel Testing ◽  
Transonic Wind Tunnel ◽  
Tunnel 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.

Evaluation of Surface Finish Affect on Aerodynamic Coefficients of Wind Tunnel RP Models Production with ABSi Material

2008 ◽  
Vol 594 ◽  
pp. 255-260 ◽  
Author(s):  
A. Ahmadi Nadooshan ◽  
Saeed Daneshmand ◽  
C. Aghanajafi
Keyword(s):  
Wind Tunnel ◽  
Rapid Prototyping ◽  
Layer Thickness ◽  
Axial Force ◽  
Normal Force ◽  
Aerodynamic Characteristics ◽  
Wind Tunnel Testing ◽  
Aerodynamic Coefficients ◽  
Fused Deposition ◽  
Tunnel Testing

Nowadays, rapid prototyping (RP) methods are widely used to produce wind tunnel testing models and thickness of layers is an important parameter that affects the aerodynamic characteristics of model. This paper described the Affects layer thickness models product with rapid prototyping on Aerodynamic Coefficients for Constructed wind tunnel testing models. Three models were evaluated. These models were fabricated from ABSi by a fused deposition method (FDM). The layer thickness was 0.178mm, 0.254mm and 0.33mm. The roughness of surfaces for each model was 25/m, 63/m and 160/m (RZ) that determined by perthometer2. A wing-body-tail configuration was chosen for the actual study. Testing covered the Mach range of Mach 0.3 to Mach 1.2 at an angle-of-attack range of -4° to +16° at zero sideslip. Coefficients of normal force, axial force, pitching moment, and lift over drag are shown at each of these Mach numbers. Results from this study show that layer thickness does have an effect on the aerodynamic characteristics in general; the data differ between the three models by fewer than 6%. The layer thickness does have more effect on the aerodynamic characteristics when Mach number is decreased and had most effect on the aerodynamic characteristics of axial force and its derivative coefficients.

Automated wind tunnel testing

1998 ◽  
Author(s):  
William Schoenfeld ◽  
Francis Priolo
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Testing ◽  
Tunnel Testing
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