Improvements on computations of high speed propeller unsteady aerodynamics

Bousquet, Jean-Marc; Gardarein, P.

doi:10.1016/s1270-9638(03)00046-4

Cited by 28 publications

(16 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For the wingtip without propeller, research has shown that RANS CFD is capable of predicting the wingtip vortex with sufficient detail, although the large gradients in flow variables require locally dense grids [8]. For conventional wing-mounted tractor propellers, RANS CFD has proven to capture the transient propeller-wing interaction effects with adequate detail [9][10][11]. When the propeller is moved to the tip of the wing, the complexity of the flowfield increases due to the interaction of the propeller blade vortices and wingtip vortex, necessitating an evaluation of the accuracy of RANS simulations for this particular configuration.…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2019

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

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

et al. 2019

View full text Add to dashboard Cite

“…With the advances of computational fluid-dynamics, the aerodynamic load prediction broadened considerably, extending the data availability up to the supersonic regime and leading toward the coupling of computational structural dynamics (CSD) and computational fluid-dynamics (CFD) (a comprehensive review was compiled by Datta et al 2007 with specific application to helicopters). Despite the rapid growth of methodologies to model a broad range of phenomena such as 3D transonic effects and dynamic stall, the co-occurrence of high Reynolds numbers with compressibility usually represents a challenge for the accurate computation of the velocity flow field (Bousquet and Gardarein 2003).…”

Section: Introductionmentioning

confidence: 99%

3D pressure imaging of an aircraft propeller blade-tip flow by phase-locked stereoscopic PIV

2011

View full text Add to dashboard Cite

The flow field at the tip region of a scaled DHC Beaver aircraft propeller, running at transonic speed, has been investigated by means of a multi-plane stereoscopic particle image velocimetry setup. Velocity fields, phase-locked with the blade rotational motion, are acquired across several planes perpendicular to the blade axis and merged to form a 3D measurement volume. Transonic conditions have been reached at the tip region, with a revolution frequency of 19,800 rpm and a relative free-stream Mach number of 0.73 at the tip. The pressure field and the surface pressure distribution are inferred from the 3D velocity data through integration of the momentum Navier-Stokes equation in differential form, allowing for the simultaneous flow visualization and the aerodynamic loads computation, with respect to a reference frame moving with the blade. The momentum and pressure data are further integrated by means of a contour-approach to yield the aerodynamic sectional force components as well as the blade torsional moment. A steady Reynolds averaged Navier-Stokes numerical simulation of the entire propeller model has been used for comparison to the measurement data.

show abstract

“…5) However, the precise analysis and evaluation of the disturbance in aerodynamic terms, particularly in the unsteady sense, cannot be achieved without precisely simulating the relative motion between the propeller and the wing. Bousquet and Gardarein 6) from ONERA managed to simulate the flow situation of a propeller-driven transport aircraft by using a multi-zone grid to solve the Euler equation. Stuermer et al 7,8) from DLR used the chimera grid to simulate the slipstream of the propeller.…”

Section: Introductionmentioning

confidence: 99%

Unsteady Numerical Simulation of the Mutual Disturbance between Propeller and Wing

Qiao

2015

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

This paper presents the unsteady numerical simulation and analysis of the slipstream generated by distributed propellers on a solar-powered UAV using the CFD method based on structured/unstructured hybrid grids. Sliding mesh technology and a transition model are used for the numerical simulation of a NACA propeller and an Eppler 387 airfoil, the results of which are well compatible with the experimental data, proving the calculation method to be highly credible and accurate. Numerical simulations are run for configurations with the propeller in front of and behind the wing, and comparative analyses are conducted with a pure propeller and pure wing. The results suggest the existence of mutual disturbance between the propeller and the wing, as the propeller, either in front of or behind the wing, causes an increase in cyclical fluctuation of the wing's lift, drag and nose-down moment. The wing, in return, gives rise to an increase in fluctuation of the propeller's pulling force, absorbing power and efficiency, with propeller oscillation being triggered by the discontinuity of the flow field. The configuration with the propeller posed behind the wing is proven to be of smaller disturbance to the whole system.

show abstract

Improvements on computations of high speed propeller unsteady aerodynamics

Cited by 28 publications

References 5 publications

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

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

3D pressure imaging of an aircraft propeller blade-tip flow by phase-locked stereoscopic PIV

Unsteady Numerical Simulation of the Mutual Disturbance between Propeller and Wing

Contact Info

Product

Resources

About