A Hybrid Viscous/Potential Flow Method for the Prediction of the Performance of Podded and Ducted Propellers

2009 ◽  
Author(s):  
Spyros A. Kinnas ◽  
Shu-Hao Chang ◽  
Yi-Hsiang Yu ◽  
Lei He
Keyword(s):  
Viscous Flow ◽  
Lattice Method ◽  
Viscous Potential Flow ◽  
Flow Solver ◽  
Vortex Lattice Method ◽  
Ducted Propeller ◽  
Hybrid Numerical Method ◽  
Convergence Study ◽  
Effective Wake ◽  
Ducted Propellers

This paper presents the analysis of the performance for podded and ducted propellers using a hybrid numerical method, which couples a vortex lattice method (MPUF-3A) for the unsteady analysis of propellers and a viscous flow solver (NS-3X or FLUENT) for the prediction of the viscous flow around propulsors and the drag force on the pod and duct surfaces. The time averaged propeller force distributions are considered as source terms (body force) in the momentum equations of NS-3X and FLUENT. The effects of viscosity on the effective wake and on the performance of the propeller blade, as well as on the predicted pod and duct forces, are assessed. The convergence study of circulation distributions with number of lattices is reported in the ducted propeller case. Finally, the prediction of the performance for podded propellers (both single pull-type and twin-type) and ducted propellers from the present method is validated against existing experimental data.

A Hybrid Viscous/Potential Flow Method for the Prediction of the Wetted and Cavitating Performance of Ducted Propellers

2015 ◽  
Author(s):  
Spyros A. Kinnas ◽  
Chan-Hoo Jeon ◽  
Ye Tian
Keyword(s):  
Present Method ◽  
Vortex Lattice ◽  
Navier Stokes ◽  
Propeller Blade ◽  
Lattice Method ◽  
Viscous Potential Flow ◽  
Vortex Lattice Method ◽  
Hybrid Numerical Method ◽  
Effective Wake ◽  
Ducted Propellers

This paper presents the analysis of the performance for various ducted propellers using a hybrid numerical method, which couples a vortex lattice method (VLM) for the analysis of propellers and a Reynolds-Averaged Navier-Stokes solver for the prediction of the viscous fluid flow around the duct. The effects of viscosity on the effective wake and on the performance of the propeller blade, as well as on the predicted duct forces, are assessed. The prediction of the performance for those ducted propellers from the present method is validated against existing experimental data.

A Hybrid Viscous/Potential Flow Method for the Prediction of the Wetted and Cavitating Performance of Ducted Propellers

2012 ◽  
Author(s):  
Spyros A. Kinnas ◽  
Chan-Hoo Jeon ◽  
Ye Tian
Keyword(s):  
Present Method ◽  
Vortex Lattice ◽  
Navier Stokes ◽  
Propeller Blade ◽  
Lattice Method ◽  
Viscous Potential Flow ◽  
Vortex Lattice Method ◽  
Hybrid Numerical Method ◽  
Effective Wake ◽  
Ducted Propellers

This paper presents the analysis of the performance for various ducted propellers using a hybrid numerical method, which couples a vortex lattice method (VLM) for the analysis of propellers and a Reynolds-Averaged Navier-Stokes solver for the prediction of the viscous fluid flow around the duct. The effects of viscosity on the effective wake and on the performance of the propeller blade, as well as on the predicted duct forces, are assessed. The prediction of the performance for those ducted propellers from the present method is validated against existing experimental data.

Comprehensive Design Method for Open or Ducted Propellers for Underwater Vehicles

2021 ◽  
Author(s):  
Spyros A. Kinnas ◽  
Kyungjung Cha ◽  
Seungnam Kim
Keyword(s):  
Design Method ◽  
A Priori ◽  
Optimization Method ◽  
Underwater Vehicles ◽  
Current Approach ◽  
Lattice Method ◽  
B Spline ◽  
Effective Wake ◽  
Propeller Thrust ◽  
Ducted Propellers

A comprehensive method which determines the most efficient propeller blade shapes for a given axisymmetric hull to travel at a desired speed, is presented. A nonlinear optimization method is used to design the blade, the shape of which is defined by a 3-D B-spline polygon, with the coordinates of the B-spline control points being the parameters to be optimized for maximum propeller efficiency, for given effective wake and propeller thrust. The performance of the propeller within the optimization scheme is assessed by a vortex-lattice method (VLM). To account fully for the hull/propeller interaction, the effective wake to the propeller and the hull resistance are determined by analyzing the designed propeller geometry by the VLM, coupled with a Reynolds-Averaged Navier-Stokes (RANS) solver. The optimization method re-designs the optimum blade with the updated effective wake and propeller thrust (taken to be equal to the updated hull resistance), and the procedure continues until convergence of the propeller performance. The current approach does not require knowledge of the wake fraction or the thrust deduction factor, both of which must be estimated a priori in traditional propeller design. The method is applied for a given hull to travel at a desired speed, and the optimum blades are designed for various combinations of propeller diameter and RPM, in the case of open and ducted propellers with provided duct shapes. The effects of the propeller diameter and RPM on the designed propeller thrust, torque, propeller efficiency, and required power are presented and compared with each other in the case of open and ducted propellers. The present approach is shown to provide guidance on the design of propulsors for underwater vehicles, and is applicable to the design of propulsors for surface ships.

Prediction of Unsteady Effective Wake by a Euler Solver/Vortex-Lattice Coupled Method

2003 ◽  
Vol 47 (02) ◽  
pp. 131-144
Author(s):  
Jin-Keun Choi ◽  
Spyros A. Kinnas
Keyword(s):  
Vortex Lattice ◽  
Three Dimensional ◽  
Lattice Method ◽  
Coupled Method ◽  
Vortex Lattice Method ◽  
Finite Volume Approach ◽  
Euler Solver ◽  
Effective Wake ◽  
Total Velocity ◽  
Surface Vortex

A fully three-dimensional Euler solver, based on a finite volume approach, is developed and applied to the prediction of the unsteady effective wake for propellers subject to non-axisymmetric inflows. The Euler solver is coupled with an existing lifting-surface vortex-lattice method for the computation of unsteady propeller flows. The coupled method is validated against the uniform inflow case, in which ideally the uniform flow should be recovered as the effective wake. The predicted total velocity field correlates very well with that measured in the water tunnel experiment. Lastly, the unsteady effective wake predicted by the present method is compared with the steady effective wake predicted by the authors' previous steady method.

Flapping wings in line formation flight: a computational analysis

2014 ◽  
Vol 118 (1203) ◽  
pp. 485-501 ◽  
Author(s):  
M. Ghommem ◽  
V. M. Calo
Keyword(s):  
Power Consumption ◽  
Aerodynamic Performance ◽  
Formation Flight ◽  
Flapping Wings ◽  
Line Formation ◽  
Lattice Method ◽  
Flow Solver ◽  
Vortex Lattice Method ◽  
Bird Evolution ◽  
Unsteady Effects

AbstractThe current understanding of the aerodynamics of birds in formation flights is mostly based on field observations. The interpretation of these observations is usually made using simplified aerodynamic models. Here, we investigate the aerodynamic aspects of formation flights. We use a potential flow solver based on the unsteady vortex lattice method (UVLM) to simulate the flow over flapping wings flying in grouping arrangements and in proximity of each other. UVLM has the capability to capture unsteady effects associated with the wake. We demonstrate the importance of properly capturing these effects to assess aerodynamic performance of flapping wings in formation flight. Simulations show that flying in line formation at adequate spacing enables significant increase in the lift and thrust and reduces power consumption. This is mainly due to the interaction between the trailing birds and the previously-shed wake vorticity from the leading bird. Moreover, enlarging the group of birds flying in formation further improves the aerodynamic performance for each bird in the flock. Therefore, birds get significant benefit of such organised patterns to minimise power consumption while traveling over long distances without stop and feeding. This justifies formation flight as being beneficial for bird evolution without regard to potential social benefits, such as, visual and communication factors for group protection and predator evasion.

Prediction of Non-Axisymmetric Effective Wake by a Three-Dimensional Euler Solver

2001 ◽  
Vol 45 (01) ◽  
pp. 13-33
Author(s):  
Jin-Keun Choi ◽  
Spyros A. Kinnas
Keyword(s):  
Vortex Lattice ◽  
Three Dimensional ◽  
Lattice Method ◽  
Vortex Lattice Method ◽  
Actuator Disk ◽  
Finite Volume Approach ◽  
Euler Solver ◽  
Effective Wake ◽  
Total Velocity ◽  
Surface Vortex

A fully three-dimensional Euler solver, based on a finite volume approach, is developed and applied to the prediction of the effective wake for propellers subject to non-axisymmetric inflows. The method is coupled with an existing lifting-surface vortex-lattice method for the analysis of unsteady cavitating propeller flows. The results are validated against analytical solutions from actuator disk theory. The effect of the grid parameters on the results (circumferential average and amplitudes of harmonics of the predicted effective wake) is found to be very weak. The predicted total velocity field correlates very well with that measured in propeller experiments.

On the Accurate Calculation of Effective Wake/Application to Ducted Propellers

2014 ◽  
Vol 58 (02) ◽  
pp. 70-82
Author(s):  
Ye Tian ◽  
Chan-Hoo Jeon ◽  
Spyros A. Kinnas
Keyword(s):  
Numerical Simulation ◽  
Potential Flow ◽  
Navier Stokes ◽  
Experimental Measurements ◽  
Control Points ◽  
Interpolation Scheme ◽  
Accurate Calculation ◽  
Flow Solver ◽  
Effective Wake ◽  
Ducted Propellers

A hybrid method that couples a potential flow solver with a Reynolds-Averaged Navier-Stokes (RANS) solver for calculating the effective wake of a propeller is proposed. Two improvements are addressed in this method:a conservative interpolation scheme that conserves the total forces when passing information from the potential flow solver to the RANS solver; anda novel option that evaluates the effective wake at the control points in the blade zone. The proposed method is first assessed in the case of an open propeller subject to uniform inflow and then applied to predict the performance of the ducted propellers under uniform inflow. The results of the numerical simulation are correlated with available experimental measurements.

Generalized vortex lattice method for planar supersonic flow

AIAA Journal ◽  
1997 ◽  
Vol 35 ◽  
pp. 1230-1233
Author(s):  
Paulo A. O. Soviero ◽  
Hugo B. Resende
Keyword(s):  
Supersonic Flow ◽  
Vortex Lattice ◽  
Lattice Method ◽  
Vortex Lattice Method

A multigrid and upwind viscous flow solver on 3-D embedded and overlapped grids

1989 ◽  
Author(s):  
OKTAY BAYSAL ◽  
KAMRAN FOULADI ◽  
VICTOR LESSARD
Keyword(s):  
Viscous Flow ◽  
Flow Solver

scholarly journals Static Aeroelastic Characteristics of Morphing Trailing-Edge Wing Using Geometrically Exact Vortex Lattice Method

2019 ◽  
Vol 2019 ◽  
pp. 1-15
Author(s):  
Sen Mao ◽  
Changchuan Xie ◽  
Lan Yang ◽  
Chao Yang
Keyword(s):  
Vortex Lattice ◽  
Deflection Angle ◽  
Aircraft Design ◽  
Analysis Method ◽  
Lattice Method ◽  
Trailing Edge ◽  
Vortex Lattice Method ◽  
Analysis And Design ◽  
Aeroelastic Analysis ◽  
Typical Model

A morphing trailing-edge (TE) wing is an important morphing mode in aircraft design. In order to explore the static aeroelastic characteristics of a morphing TE wing, an efficient and feasible method for static aeroelastic analysis has been developed in this paper. A geometrically exact vortex lattice method (VLM) is applied to calculate the aerodynamic forces. Firstly, a typical model of a morphing TE wing is chosen and built which has an active morphing trailing edge driven by a piezoelectric patch. Then, the paper carries out the static aeroelastic analysis of the morphing TE wing and corresponding simulations were carried out. Finally, the analysis results are compared with those of a traditional wing with a rigid trailing edge using the traditional linearized VLM. The results indicate that the geometrically exact VLM can better describe the aerodynamic nonlinearity of a morphing TE wing in consideration of geometrical deformation in aeroelastic analysis. Moreover, out of consideration of the angle of attack, the deflection angle of the trailing edge, among others, the wing system does not show divergence but bifurcation. Consequently, the aeroelastic analysis method proposed in this paper is more applicable to the analysis and design of a morphing TE wing.

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