Solution-based adaptive mesh redistribution applied to harmonic balance solvers

Djeddi, Reza; Ekici, Kivanc

doi:10.1016/j.ast.2018.11.003

Cited by 8 publications

(2 citation statements)

References 42 publications

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“…Structured meshes were considered, but were not possible in the timeframe of the project and would not be expected to offer significant increases in accuracy in this case. Attention needs to be taken when choosing the prism layer thickness and first element height [34,52,53]. To evaluate the boundary layer thickness, the Reynolds number needs to be calculated by…”

Section: Computational Mesh Sensitivity Investigationsmentioning

confidence: 99%

Unsteady Detached-Eddy Simulation (DES) of the Jetstream 31 aircraft in One Engine Inoperative (OEI) condition with propeller modelling

Casadei

Könözsy

Lawson

2019

Aerospace Science and Technology

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Numerical results from a three-dimensional (3D) computational fluid dynamics (CFD) model of the Jetstream 31 aircraft in conditions of one engine inoperative are presented. The objective of this work is to analyse the performance of the Jetstream 31 aircraft and provide transient data using an unsteady Detached-Eddy Simulation (DES) CFD approach and a numerical propeller model to compare computational results with a single engine flight test experiment. The propeller modelling approach has been implemented through User-Defined Functions using C programming language to replicate the propeller effect. Different angles of attack and sideslip are studied, based on records from flight test data, both with unsteady (DES) and steady-state Reynolds-Averaged Navier-Stokes (RANS) models. An error analysis on the flight test data provides an error band from 2% to 16% among all cases, high values due to the lack of many data samples. Across the RANS approach, an average deviation of 6.9% and 3.8% for respectively lift and drag coefficients is achieved. By applying the DES turbulence modelling approach, a better lift prediction is achieved (5.4%) despite a slightly worse drag (4.5%). It has also been found that 80% of the numerical results are within the error band defined. A close agreement has been found within moment coefficients, with average percentage deviations from 3.3% to 7.0%. Overall, an analysis has been carried out in the present work, both on the flight test and computational sides to provide reliable numerical results of these aerodynamic properties.

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Section: Computational Mesh Sensitivity Investigationsmentioning

confidence: 99%

Unsteady Detached-Eddy Simulation (DES) of the Jetstream 31 aircraft in One Engine Inoperative (OEI) condition with propeller modelling

Casadei

Könözsy

Lawson

2019

Aerospace Science and Technology

View full text Add to dashboard Cite

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“…17 For the reduction of discrete errors for continuity equations, an adaptive mesh technique could efficiently cluster the grid nodes in sensitive regions by redistribution and relocation of the grid nodes. 18 The electromagnetic scattering characteristics of helicopters mainly come from the fuselage, rotor and tail rotor, [19][20][21] where the rotor components are the most important scattering sources of dynamic RCS. Although the aerodynamic characteristics of highspeed rotating rotors have made great progress, 21,22 their research methods on real-time and dynamic RCS characteristics still need to be developed, 23 which is a further development of the sports target RCS research.…”

Section: Introductionmentioning

confidence: 99%

Grid transformation and dynamic scattering for tail rotor radar cross section analysis

Zhou

Huang

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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With the promotion and enhancement of stealth technology of helicopter rotor components, the research on the dynamic radar cross section (RCS) of helicopter rotor is becoming more and more important and imminent. In order to facilitate the calculation and analysis of the electromagnetic scattering characteristics during rotor rotation, a dynamic scattering calculation (DSC) method based on quasi-static principle (QSP) and grid coordinate transformation is presented. After analyzing the advantages and disadvantages of QSP, the dynamic principle is used to describe the rotation process of the rotor. Combined with the grid coordinate transformation method, the RCS of the rotor is accurately calculated by physical optics (PO) and physical theory of diffraction (PTD). Then the influence of azimuth, elevator angle and observation distance on rotor dynamic RCS is analyzed. The results show RCS of the tail rotor is indeed dynamic and periodic and its main influencing factors include azimuth and elevation angle. The proposed DSC method is efficient and effective for studying the dynamic RCS of tail rotor.

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FDOT: A Fast, memory-efficient and automated approach for Discrete adjoint sensitivity analysis using the Operator overloading Technique

Djeddi

Ekici

2019

Aerospace Science and Technology

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Solution-based adaptive mesh redistribution applied to harmonic balance solvers

Cited by 8 publications

References 42 publications

Unsteady Detached-Eddy Simulation (DES) of the Jetstream 31 aircraft in One Engine Inoperative (OEI) condition with propeller modelling

Unsteady Detached-Eddy Simulation (DES) of the Jetstream 31 aircraft in One Engine Inoperative (OEI) condition with propeller modelling

Grid transformation and dynamic scattering for tail rotor radar cross section analysis

FDOT: A Fast, memory-efficient and automated approach for Discrete adjoint sensitivity analysis using the Operator overloading Technique

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