Validation and Comparison of RANS Propeller Modeling Methods for Tip-Mounted Applications

Stokkermans, T.C.A.; Arnhem, Nando van; Sinnige, Tomas; Veldhuis, L.L.M.

doi:10.2514/1.j057398

Cited by 77 publications

(48 citation statements)

References 27 publications

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“…A detailed discussion of the numerical setup, including grid-dependency studies, is provided in Ref. [18]. This reference also compares the actuator-disk results to data obtained from simulations with fully-resolved blades and simulations with an actuator-line model.…”

Section: Cfd Simulations With Rans Solvermentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamic Performance of a Wingtip-Mounted Tractor Propeller Configuration in Windmilling and Energy-Harvesting Conditions

Sinnige

Stokkermans

Arnhem

et al. 2019

AIAA Aviation 2019 Forum

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Section: Cfd Simulations With Rans Solvermentioning

confidence: 99%

“…The validity of the simulation approach was shown before in Refs. [18,27] and is, therefore, not discussed in the present paper.…”

Section: B Installed Performancementioning

confidence: 99%

Aerodynamic Performance of a Wingtip-Mounted Tractor Propeller Configuration in Windmilling and Energy-Harvesting Conditions

Sinnige

Stokkermans

Arnhem

et al. 2019

AIAA Aviation 2019 Forum

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“…Finally, the simulations are performed using the Spalart-Almaras one-equation eddy viscosity model [17]. The curvature correction option is incorporated as well as the strain/vorticity-based production term, proposed by Dacles-Mariani et al [18], to prevent build-up of turbulence viscosity in vortex cores [19].…”

Section: Comparison To Cfd Resultsmentioning

confidence: 99%

Experimental Aerodynamic Analysis of a 4.6%-Scale Flying-V Subsonic Transport

Palermo

Vos

2020

AIAA Scitech 2020 Forum

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The experimental investigation into the aerodynamic characteristics of a 4.6%-scale half-model of a flying-wing transport aircraft is detailed. The study is performed in an open-jet wind tunnel where forces and moments are recorded using a 6-axis balance. Two control surfaces in the outboard wing are deflected to measure their effect in terms of lift, drag, and pitching moment up to a Reynolds number of 1 million. The results are subsequently combined with the estimated thrust force using a flight mechanics model of the aircraft in order to predict the most forward and most aft center-of-gravity locations for which the aircraft can be balanced with the control surfaces, while still being statically stable. The results show that the aircraft can attain an untrimmed maximum lift coefficient of 1.02 at an angle of attack of 35 degrees. Furthermore, the pitching moment around the leading-edge of the mean geometric chord is negatively correlated to the angle of attack up to 19 degrees, after which a strong pitch-break is observed, making the aircraft statically unstable. This is associated with a forward shift of the aerodynamic center to a longitudinal position 35%c ahead of the moment reference point which is caused by the formation of strong vortices over the wing surface. The effectiveness of the control surfaces hardly deteriorates with angle of attack and all three control surfaces are shown to be effective up to the maximum lift coefficient. Analysis shows that the center-ofgravity location should reside between [-7.5; 0.5] %c, in power-off conditions, and between [-6; 1] %c, in power-on conditions, from the leading edge of the mean geometric chord to ensure an ultimate static stability margin of 4.4% as well and a minimum landing speed of 20 m/s. Within these ranges, trimmed maximum lift coefficient values of 0.68 and 0.66 can be achieved respectively in power-off and power-on conditions.

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“…The AD model applied in this study was developed at TU Delft, and has been subjected to a validation study in Ref. [29]. The AD imposes an axial momentum, tangential momentum and energy jump at the propeller location, as described in Ref.…”

Section: Propeller Modelling Methodsmentioning

confidence: 99%

“…The AD imposes an axial momentum, tangential momentum and energy jump at the propeller location, as described in Ref. [29]. Thus, the AD requires the thrust and torque of the propeller as inputs.…”

Section: Propeller Modelling Methodsmentioning

confidence: 99%

Aerodynamic Performance and Interaction Effects of Circular and Square Ducted Propellers

Bento

Vries

Veldhuis

2020

AIAA Scitech 2020 Forum

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Ducted propellers constitute an efficient propulsion-system alternative to reduce the environmental impact of aircraft. These systems are able to increase the thrust-to-power ratio of a propeller system by both producing thrust and by lowering tip losses of propellers. In this research, steady and unsteady RANS CFD simulations were used to analyze the possible impact of modifying a propeller duct shape from a circular to a square geometry. Initially, the two duct designs and the propeller were studied separately, in order to estimate the numerical errors and to compare with existing data. In the installed simulations, the propeller was first modelled as an actuator disk, and afterwards with a full blade model, in order to understand the time-averaged influence of the propeller on the duct before studying the complete unsteady propeller-duct interaction. In the current design, the square duct corners were found to be prone to separation, and to contribute towards the generation of strong vortices. Furthermore, due to the reduced leading-edge suction on the square duct, the square ducted system was found to be 4.5% less efficient than the circular one, for the conditions tested. By relating the aerodynamic interaction phenomena to the performance of the system, this study provides and important basis for the design of unconventional ducted systems.

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Validation and Comparison of RANS Propeller Modeling Methods for Tip-Mounted Applications

Cited by 77 publications

References 27 publications

Aerodynamic Performance of a Wingtip-Mounted Tractor Propeller Configuration in Windmilling and Energy-Harvesting Conditions

Aerodynamic Performance of a Wingtip-Mounted Tractor Propeller Configuration in Windmilling and Energy-Harvesting Conditions

Experimental Aerodynamic Analysis of a 4.6%-Scale Flying-V Subsonic Transport

Aerodynamic Performance and Interaction Effects of Circular and Square Ducted Propellers

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