The rapid and robust generation of efficient hybrid grids for rans simulations over complete aircraft

Shaw, J. A.; Stokes, S.; Lucking, M. A.

doi:10.1002/fld.497

Cited by 22 publications

(4 citation statements)

References 14 publications

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“…Meshes were generated using the Solar mesher [9]. Due to both propellers spinning in the same direction all simulations required meshing of the full aircraft.…”

Section: Meshingmentioning

confidence: 99%

Comparison of Aircraft Loads Using URANS and Actuator Disk Modelling of Propellers at High Incidence

Wales

Jones

Gaitonde

et al. 2023

AIAA AVIATION 2023 Forum

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A comparison of simulations are performed using both steady RANS with an actuator disk model to represent the propellers and URANS with full rotating blade geometry, for the Clean Sky 2 flying test bed 2, which is a regional turboprop with co-rotating propellers. The simulations are performed for a cruise configuration at Mach 0.2 and a Reynolds number of 11.933 × 10 6 for a range of angles of attack and side slip angles from zero to 20 𝑜 and 25 𝑜 respectively. The generation of the database for the actuator disk model is explained, along with the calibration of the blade angle to give a specified thrust. Aerodynamic coefficients for both the airframe and the propellers are extracted and compared with wind-tunnel data from an atmospheric wind-tunnel test undertaken in a previous Clean Sky 2 project (ReLOAD).

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“…Meshes were generated using the Solar mesher [9]. Due to both propellers spinning in the same direction all simulations required meshing of the full aircraft.…”

Section: Meshingmentioning

confidence: 99%

Comparison of Aircraft Loads Using URANS and Actuator Disk Modelling of Propellers at High Incidence

Wales

Jones

Gaitonde

et al. 2023

AIAA AVIATION 2023 Forum

View full text Add to dashboard Cite

show abstract

“…Meshes were generated using the Solar mesher [7]. Due to both propellers spinning in the same direction all simulations required meshing of the full aircraft.…”

Section: Meshingmentioning

confidence: 99%

Comparison of Aircraft Loads Using URANS and Actuator Disk Modelling of Propellers

Wales

Jones

Gaitonde

et al. 2022

AIAA AVIATION 2022 Forum

View full text Add to dashboard Cite

A comparison of simulations are performed using both steady RANS with an actuator disk model to represent the propellers and URANS with full rotating blade geometry, for the Clean Sky 2 flying test bed 2, which is a regional turboprop with co-rotating propellers. The simulations are performed for a cruise configuration at Mach 0.2 and a Reynolds number of 11.933 × 10 6 for a range of angles of attack and side slip angles. The generation of the database for the actuator disk model is explained, along with the calibration of the blade angle to give a specified thrust. Aerodynamic coefficients for both the airframe and the propellers are extracted and compared with wind-tunnel data from an atmospheric wind-tunnel test undertaken in a previous Clean Sky 2 project (ReLOAD).

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“…For each case, the markers in each image were identified and then used in the process of projecting the image onto the mesh. The mesh required for the TSP post-processing was generated using the CFD mesh generation suite Solar (2) . A quad-dominant isotropic mesh was generated and converted to triangles, before being converted to the Tecplot dat file format required by the TSP processing software.…”

Section: Tsp Post-processingmentioning

confidence: 99%

Qualification of the ARA TWT for laminar flow testing

Allen

Lawson

Maina

et al. 2014

Aeronaut. j. (1968)

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The current drive towards reducing the environmental impact of aircraft necessitates the ability to evaluate techniques for promoting natural laminar flow in a large scale wind tunnel facility. A test was undertaken on the M2355 variable sweep model to obtain temperature sensitive paint (TSP) and hot-film data from which the transition locations at a range of sweep angles and flow conditions could be identified. The TSP technique has been shown to be a reliable method for determining transition on suitably treated wind tunnel models. Pressure data were also acquired and interpolated to provide the input to the laminar boundary layer code, BL2D, the output from which was used in the linear stability analysis code, CoDS, to calculate the N-factor for the ARA TWT (Transonic Wind Tunnel) facility. Two sets of N-factors were calculated, firstly using incompressible analysis with stationary crossflow and secondly using compressible analysis with travelling crossflow. In both analyses the Tollmien-Schlichting and crossflow cases were calculated together, rather than separating the cases before running the analysis. The resulting N-factors indicate a degree of scatter typical for experimental data. The N-factor based on incompressible theory for crossflow was found to be approximately 7 and for Tollmien-Schlichting (T-S), approximately 11. The results of the wind tunnel test and the analysis carried out are considered to be the first steps towards establishing a methodology for performance testing, in atmospheric tunnels such as the TWT, for aircraft designed to have significant regions of laminar flow. The project has also provided a body of experimental test data which will be valuable for future research into development and validation of laminar flow methods.

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The rapid and robust generation of efficient hybrid grids for rans simulations over complete aircraft

Cited by 22 publications

References 14 publications

Comparison of Aircraft Loads Using URANS and Actuator Disk Modelling of Propellers at High Incidence

Comparison of Aircraft Loads Using URANS and Actuator Disk Modelling of Propellers at High Incidence

Comparison of Aircraft Loads Using URANS and Actuator Disk Modelling of Propellers

Qualification of the ARA TWT for laminar flow testing

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