Numerical Simulation of the F-16XL at Full-Scale Flight Test Conditions Using a Near-Body Off-Body CFD Approach

Author(s):  
Scott A. Morton ◽  
David R. McDaniel
2009 ◽  
Vol 75 ◽  
pp. 1-6 ◽  
Author(s):  
Fu Chi Wang ◽  
Qun Bo Fan ◽  
Lu Wang ◽  
Quan Sheng Wang ◽  
Zhuang Ma

To develop novel and advanced thermal barrier coatings, full-scale numerical simulation of plasma-sprayed functionally gradient materials is conducted in this paper, including the prediction of basic parameters at the nozzle exit, simulation of three dimensional simulation of the plasma jet, modeling of the interaction between the plasma jet and the particles, calculation of flight trajectories and temperature history of flying metal and ceramic particles, the interaction between the molten particles and the substrate, as well as the deposition process of the coatings. Various complex phenomena, such as turbulent effects with chemical reactions in the plasma jet, dispersion status of the particles onto the substrate, and the composition distribution of the functionally gradient materials, are fully taken into account. The numerical simulation results are found to be in good agreement with experimental evidence.


2019 ◽  
Vol 109 ◽  
pp. 00079
Author(s):  
Oleh Riabtsev ◽  
Serhii Protsak

The results of a comprehensive geomechanical prediction of the state of the host rocks in the vicinity of the development working when mining the excavation column of longwall in the vicinity of the rock inrush in the conditions of one of the mines of Western Donbas are presented. A numerical simulation of the size and shape of the rock inrush zone and a comparison of the obtained results with the full-scale mine observations were carried out using the theory of fractals and rock damageability.


Author(s):  
Juan P. Pontaza ◽  
Mohan Kotikanyadanam ◽  
Piet Moeleker ◽  
Raghu G. Menon ◽  
Shankar Bhat

It is well established that strakes are effective at suppressing vortex-induced vibrations (VIV). Fairings are an attractive alternative to helical strakes, because they are a low drag VIV suppression solution. The paper presents an evaluation of a fairing design, based on numerical simulations — to be complemented at a later stage with current tank testing. This paper documents the computational fluid dynamics (CFD) and finite element analysis (FEA) of the evaluation: (1) 3-D CFD in the laboratory scale: 4.5 inch pipe, 3 ft/s current speed, (2) 3-D CFD in the full scale: 14 inch riser, 4 knots current speed, and (3) 3-D FEA of the full-scale fairing module latching mechanism, under service loads corresponding to 4 knots current speed. The analysis results show that the fairing design (1) is effective at suppressing VIV, (2) yields a low drag coefficient (0.52 at Re ∼ 106), and (3) its latching mechanism is adequate for use in calm sea states with 4 knots current speeds.


2012 ◽  
Vol 238 ◽  
pp. 728-732
Author(s):  
Xiao Lin Yu ◽  
Bu Yu Jia ◽  
Wei Feng Wang ◽  
Quan Sheng Yan

In this paper, the construction technology for main pylon of cable-stayed bridge is researched through test of full-scale model of anchorage zone of pylon of Guangzhou Bridge. Stress distribution and deformation condition of model under prestressed tendons and cable force are analyzed. Numerical simulation on this anchorage zone model is carried out. By comparing FEM results to the test results, some important conclusions are drawn out and give some advices to the optimum design of the bridge pylon. Parts of the achievements have been applied to actual bridge work and obtained successful engineering experience.


Author(s):  
T Triantafyllou ◽  
T Nikolaidis ◽  
M Diakostefanis ◽  
P Pilidis

The aim of the study presented herein is to numerically predict the behaviour of the airflow around a flying military aircraft with an active intake in which the airflow may enter and travel all the way up to the aerodynamic interface plane (the analytical interface between the inlet and engine). Computational fluid dynamics is used as the basic tool. The geometry created consists of a full-scale military aircraft exposed to different flight conditions. The flow results are mainly focused at the aerodynamic interface plane since the present study is a part of a greater research effort to estimate how the airflow distortion induced to the engine’s face due to the aircraft’s flight attitude, affects the embedded gas turbine’s performance. The obtained results were validated through a direct comparison against similar experimental ones, collected from a wind tunnel environment.


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