CFD simulation of engine nacelle cooling on pusher configuration aircraft

Olejnik, Aleksander; Dziubiński, Adam; Kiszkowiak, Łukasz

doi:10.1108/aeat-12-2020-0290

Cited by 4 publications

(3 citation statements)

References 11 publications

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“…Two facts account for this as follows: on the one hand, as mesh size decreases, smaller time steps need to be used due to the stability criteria; on the other hand, as the artificial viscosity term is of magnitude Dx 3 , the residual which comes from artificial viscosity will decrease, which needs more iterations to shrink the DE between discretized equations with artificial viscosity and physical equations. Results (in terms of iteration steps trend) agree well with the CFD simulation of an engine nacelle by Olejnik et al (2021).…”

Section: Parametric Effects On Numerical Behaviorsupporting

confidence: 68%

Parametric and V&V study in a fundamental CFD process: revisiting the lid-driven cavity flow

Zhang

Brookshire

et al. 2021

AEAT

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Purpose The openings on aircraft structures can be modeled from an aerodynamical point of view as lid-driven cavities (LDC). This paper aims to show the primary verification and validation (V&V) process in computational fluid dynamics (CFD, and to investigate the influences of numerical settings on the efficiency and accuracy for solving the LDC problem. Design/methodology/approach To dig into the details of CFD approaches, this paper outlines the design, implementation, V&V and results of an efficient explicit algorithm. The parametric study is performed thoroughly focusing on various iteration methods, grid density discretization terms and Reynolds number effects. Findings This study parameterized the numerical implementation which provides empirical insights into how computational accuracy and efficiency are affected by changing numerical settings. At a low Reynolds number (not over 1,000), the time-derivative preconditioning is necessary, and k = 0.1 can be the optimal value to guarantee the efficiency, as well as the stability. A larger artificial viscosity (c = 1/16) would relieve the calculating oscillation issue but proportionally increase the discretization error. Furthermore, the iteration method and the mesh quality are two key factors that affect the convergence efficiency, thus need to be selected “wisely”. Practical implications The study shows how numerical implementation can enhance an accurate and efficient solution. This workflow can be used to determine the best parameter settings whenever CFD researchers applying this LDC problem as a complementary design tool for testing newly developed solvers. Originality/value The studied LDC problem is representative of CFD analysis in real aircraft structures. These numerical simulations provide a cost-effective and convenient tool to understand the parameter sensitivity, solution receptivity and physics of the CFD process.

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Section: Parametric Effects On Numerical Behaviorsupporting

confidence: 68%

Parametric and V&V study in a fundamental CFD process: revisiting the lid-driven cavity flow

Zhang

Brookshire

et al. 2021

AEAT

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“…The calculations were performed using ANSYS Fluent software based on the solution of partial differential equations by the finite volume methods (Hirsch, 1988; Goraj et al , 2021). The software used allows the analysis of incompressible and compressible flows, with optional consideration of flow viscosity (Ferziger and Peric, 2002; Olejnik et al , 2021a, 2021b). When performing numerical aerodynamic analyses in symmetric flow, the symmetry of the flow field was assumed and the flow was assumed to be stationary and stabilized, i.e.…”

Section: System Testsmentioning

confidence: 99%

“…However, in the absence of geometric data of the aircraft components, the first step is to digitize the real object. It consists in transferring the geometry of the aircraft to virtual reality using reverse engineering (RE) methods (Olejnik et al, 2021a(Olejnik et al, , 2021b. The result of this process is usually a set of points (a so-called point cloud) defining the external outline.…”

Section: System Testsmentioning

confidence: 99%

Combat aircraft as airborne launch platforms for space rockets

Olejnik

Zalewski²,

Kiszkowiak³

et al. 2022

AEAT

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Purpose The purpose of this study was to analyze the possibility of using combat aircraft including decommissioned as a platform for launching and carrying space rockets with satellites (nano and microsatellites). Thus, an airborne-launcher-to-space-system may be attractive to countries without ground-based space rocket launch sites. Design/methodology/approach For considered launch-to-orbit system configurations, simulations of space rocket effects on aerodynamic characteristics were performed using computational fluid dynamics (CFD ANSYS Fluent) methods. In addition, experimental studies were performed in a wind tunnel to verify the numerical simulations. Discrete models of the aircraft structure were developed for analysis using finite element method (FEM). The analysis of simulated structural properties of the models was carried out to test its stiffness and mass characteristics important for solving the static and dynamic problems of the structure. The validation analyses of aircraft models were based on mass distribution estimation and matching the stiffness properties of the individual airframe structural assemblies. Findings The results of numerical analyses and tunnel tests indicate that the influence of carrier rockets on the change of aerodynamic and strength characteristics of the airframe is rather negligible. The aircraft can be used as launching platforms for space rockets. Simulations have indicated that the aircraft will successfully perform a mission of taking away and launching a rocket of at least about 1,000 kg total weight with a 10 kg space payload included. Practical implications The combat aircraft can be used as launch platforms for space rockets, and the air/rocket set can become the equivalent of responsive space assets for countries with small space budgets. Originality/value The work presents original results obtained by the authors during a preliminary design of a low-cost satellite launch system consisting of a carrier aircraft and a space rocket orbiter. The possibility of using decommissioned combat aircraft as air-launch-to-orbit platforms was taken into consideration. In the absence of aircraft design documentation, reverse engineering methods and techniques were used to develop aircraft geometry and airframe strength structure. Use of CFD, FEM and simulation methods to evaluate system capabilities was demonstrated. Numerical results from CFD simulations were finally verified in experimental tests.

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