Recent improvements in propeller aerodynamic computations

Bousquet, Jean-Marc; Gardarein, P.

doi:10.2514/6.2000-4124

Cited by 14 publications

(5 citation statements)

References 1 publication

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“…The curved lifting-line method has been chosen because it is a method commonly used in the preliminary design stages of straight and swept blades [14][15][16][17][18][19][20][21][22][23]. Although the complete method development, configuration, and validation can be found in [24], this section aims to describe the salient points and features of the lifting-line approach used.…”

Section: Lifting-line Methodsmentioning

confidence: 99%

Toward a Scalable Propeller Performance Map

Giannakakis

Laskaridis

Nikolaidis

et al. 2015

Journal of Propulsion and Power

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Propeller performance is traditionally represented by a performance map that gives propeller efficiency as a function of the flight Mach number, the power coefficient C P , and the advance ratio J. This work aims to demonstrate how this map changes when the design C P and J change and to propose a novel map format that is able to capture the performance of different propeller designs. For this purpose, the propeller performance is simulated using a propeller lifting-line method validated for the SR3 propfan. Subsequently, the propeller model is used within a sequential quadratic programming framework to optimize the blade twist and chord distribution for different sets of design C P and J. A complete propeller performance map is then generated for each one of the optimized designs. The results demonstrate that all the investigated propellers can be modeled by a common map, which determines separately the ideal efficiency and the viscous losses. The ideal efficiency is given in the traditional format of η i fC P ;J, whereas the viscous losses are represented as a function of the relative variables C P ∕C Pdes and J∕J des .

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Section: Lifting-line Methodsmentioning

confidence: 99%

Toward a Scalable Propeller Performance Map

Giannakakis

Laskaridis

Nikolaidis

et al. 2015

Journal of Propulsion and Power

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“…The propeller model (Fig. 2) was originally built for the European APIAN (Advanced Propulsion Integration Aerodynamics and Noise) [11][12][13][14] project. It features six carbon fiber blades and a rotor diameter of 0.508 m. The blade angle at 75% of the radius was set to 40.4 degrees.…”

Section: A Wind Tunnel Facility and Modelsmentioning

confidence: 99%

Aerodynamic and Aeroacoustic Effects of Pylon Trailing Edge Blowing on Pusher Propeller Installation

Sinnige

Lynch

Ragni

et al. 2015

21st AIAA/CEAS Aeroacoustics Conference

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The aerodynamic and aeroacoustic effects of pylon trailing edge blowing on the propulsive performance and noise emissions of a propeller installed in a pusher configuration were studied in a wind tunnel. A propeller model and a pylon equipped with a trailing edge blowing system were installed in the large low-speed facility of the German-Dutch wind-tunnels (DNW-LLF). Particle image velocimetry measurements of the flow field downstream of the pylon confirmed a wake re-energization obtained through blowing, with a momentum deficit recovery of 80% compared to the unblown case. For the symmetric inflow conditions considered, the effect of pylon installation on the propulsive performance was found small. Increases in thrust and torque of 1% up to 6% were measured at high and low thrust settings, which was comparable to the measurement variability. Acoustic data obtained using out-of-flow microphones confirmed the strong interaction effects resulting from the installation of the upstream pylon, with an increase in noise levels due to the presence of the pylon of up to 12 dB at a medium propeller thrust setting. The application of pylon trailing edge blowing successfully eliminated the installation effects, resulting in noise levels equal to those of the isolated propeller over the entire axial directivity range. At higher thrust settings the change in blade angle of attack due to the pylon wake impingement is smaller, and the steady blade loads are larger compared to the unsteady loads experienced during the wake passage. Consequently, in this operating regime the propeller noise emissions were dominated by steady sources for all but the most upstream observer positions.

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“…1. The six-bladed propeller model with a diameter of 0.508 m was originally developed for the European APIAN (Advanced Propulsion Integration Aerodynamics and Noise) [19][20][21][22] project. The blade angle was set to a fixed value of 40.4 degrees at 75% of the radius.…”

Section: A Wind Tunnel Facility and Modelsmentioning

confidence: 99%

The Effects of Swirl Recovery Vanes on Single-Rotation Propeller Aerodynamics and Aeroacoustics

Sinnige

Kuijk

Lynch

et al. 2015

21st AIAA/CEAS Aeroacoustics Conference

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A preliminary assessment of the aerodynamic and aeroacoustic impact of swirl recovery vanes (SRVs) installed downstream of a single-rotating propeller model was performed at the large low-speed facility of the German-Dutch wind tunnels (DNW-LLF). The SRVs are designed to recover the swirl in the rotor slipstream, thereby increasing the propulsive efficiency without the added complexity of contra-rotating systems. The performance data acquired with a rotating shaft balance showed that the upstream effect of the SRVs on the time-averaged rotor performance was negligible. Particle image velocimetry measurements in the slipstream of the propeller with and without SRVs substantiated the efficacy of the vanes in reducing the swirl in the propeller slipstream. Integrated in the radial direction, installation of the vanes reduced the swirl kinetic energy by 50% at a medium propeller thrust setting. An additional slipstream contraction was observed with vanes installed. The acoustic data measured with out-of-flow microphones showed that installation of the SRVs increased the total sound pressure levels by 2 to 6 dB compared to the isolated propeller.

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Recent improvements in propeller aerodynamic computations

Cited by 14 publications

References 1 publication

Toward a Scalable Propeller Performance Map

Toward a Scalable Propeller Performance Map

Aerodynamic and Aeroacoustic Effects of Pylon Trailing Edge Blowing on Pusher Propeller Installation

The Effects of Swirl Recovery Vanes on Single-Rotation Propeller Aerodynamics and Aeroacoustics

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