Abstract
Aircraft safety depends on wing flow process, so the study of air flow in different flight conditions is one of the most important parts of aircraft design and exploiting. The effective method of aerodynamic processes modeling is experiment in wind (aerodynamic) tunnel or water (hydrodynamic) tunnel. They allow to perform experiments with a scaled model of an aircraft affected by icing and to visualize the wing flow process and changes caused by icing. A visualization and video registration of the wing flow yields useful qualitative information about flow, but it is more important to retrieve quantitative 3D data of flow for 3D visualization and analysis. The presented study addresses to creating an image-based system for accurate 3D flow acquisition for further diverse 3D visualization and quantitate evaluation of 3D flow parameters in a hydrodynamic tunnel for aircraft icing influence exploration. Being an initial part of a long- term research project, this study is aimed at developing stereolithography (SLA) modeling technique for flow visualization in hydrodynamic tunnel and a photogrammetric system for accurate flow 3D caption. The results of first experiments of the system calibration and application are given along with preliminary results of flow jets 3D reconstruction.
Highlights
A comprehensive study of flow behavior is crucially important for aircraft performance and safety
The similitude concept allows to use liquid instead of air when studying flow behavior. Such possibility arises from the key condition of similarity real and model flow process expressed in the equivalence of main dimensionless similarity criteria such as Reynolds number, Mach number, Prandtl number
The developed image-based system for accurate 3D flow acquisition and 3D analysis utilizes a set of calibrated high-speed cameras for synchronized flow motion registration
Summary
A comprehensive study of flow behavior is crucially important for aircraft performance and safety. Physical flow modeling in aerodynamic or hydrodynamic tunnel plays important role in the process of an aircraft design due to possibility of controlled study of flow behavior for various flight conditions, including critical attack angles or wing icing [1]. The basis for such modeling is the similitude concept. The similitude concept allows to use liquid instead of air when studying flow behavior Such possibility arises from the key condition of similarity real and model flow process expressed in the equivalence of main dimensionless similarity criteria such as Reynolds number, Mach number, Prandtl number. The paper presents the developed photogrammetric system for accurate flow 3D registration and processing aimed at further 3D visualization of the flow
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