Analysis of propeller-induced aerodynamic effects

Strash, Daniel J.; Lednicer, David; Rubin, T.

doi:10.2514/6.1998-2414

Cited by 11 publications

(3 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…It provides a simplified method to simulate the propeller slipstream flow field. For instance Strash et al 4 combined momentum theory and blade element theory to create an EAD model in the numerical simulation of a propeller unit; Conway 5,6 established a nonlinear EAD model with the help of the blade element theory. They also calculated the flow field of Aurora aircraft by combining their EAD model with a panel method; and Veldhuisand Nebiolo 7 built an EAD model based on the test data of propeller models.…”

Section: Configuration and Study Of Ducted Fan Aircraftmentioning

confidence: 99%

Numerical analysis of aerodynamic characteristics for the design of a small ducted fan aircraft

Wang

Chen²,

Guo

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

This article presents a study on the flow field and aerodynamic characteristics of the propellers and rudders for the design of a small ducted fan aircraft. In the analysis, an equivalent actuation disk was created as a simplified model of the propellers. A momentum source is determined by equivalent actuation disk numerical simulation using ANSYS CFX software based on vortex theory. In addition, the momentum source distribution function for the equivalent actuation disk model is improved by using experimental data. The computational fluid dynamics method in the ANSYS CFX software is then used to simulate the flow field of the propellers slipstream and determine the key aerodynamic and design parameters for the built-up rudders of the aircraft. The improved equivalent actuation disk method is validated by using the mixing plane method and their results show a good comparison. The simulation and analysis results provide the basis for optimal design of the built-up rudder arrangement and layout for a small ducted fan aircraft.

show abstract

Section: Configuration and Study Of Ducted Fan Aircraftmentioning

confidence: 99%

Numerical analysis of aerodynamic characteristics for the design of a small ducted fan aircraft

Wang

Chen²,

Guo

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…Strash and Lednicer [1] had conducted simulations to study the aerodynamic interferences between the propeller slipstream and fuselage. The corresponding results showed that the comparisons between computed and measured wing pressure data were good and the propeller thrust coefficient was within 12% of the experiment.…”

Section: Introductionmentioning

confidence: 99%

Unsteady Aerodynamic Investigation of the Propeller-Wing Interaction for a Rocket Launched Unmanned Air Vehicle

Zhang

Chien

et al. 2013

Advances in Mechanical Engineering

View full text Add to dashboard Cite

The aerodynamic characteristics of propeller-wing interaction for the rocket launched UAV have been investigated numerically by means of sliding mesh technology. The corresponding forces and moments have been collected for axial wing placements ranging from 0.056 to 0.5 and varied rotating speeds. The slipstream generated by the rotating propeller has little effects on the lift characteristics of the whole UAV. The drag can be seen to remain unchanged as the wing's location moves progressively closer to the propeller until 0.056 away from the propeller, where a nearly 20% increase occurred sharply. The propeller position has a negligible effect on the overall thrust and torque of the propeller. The efficiency affected by the installation angle of the propeller blade has also been analyzed. Based on the pressure cloud and streamlines, the vortices generated by propeller, propeller-wing interaction, and wing tip have also been captured and analyzed.

show abstract

“…To relate the streamfunction to the regularized vorticity field rather than the singular one, a G σ function is used in place of G as follows, 16) where G σ (x) = G (|x|/σ) /σ according to Winckelmans.…”

mentioning

confidence: 99%

A Three Dimensional Vortex Particle-Panel Code For Modeling Propeller-Airframe Interaction

Calabretta¹

View full text Add to dashboard Cite

Analysis of the aerodynamic effects of a propeller flowfield on bodies downstream of the propeller is a complex task. These interaction effects can have serious repercussions for many aspects of the vehicle, including drag changes resulting in larger power requirements, stability changes resulting in adjustments to stabilizer sizing, and lift changes requiring wing planform adjustments.Historically it has been difficult to accurately account for these effects at any stage during the design process. More recently methods using Euler solvers have been developed that capture interference effects well, although they don't provide an ideal tool for early stages of aircraft design, due to computational cost and the time and expense of setting up complex volume grids. This research proposes a method to fill the void of an interference model useful to the aircraft conceptual and preliminary designer.The proposed method combines a flexible and adaptable tool already familiar to the conceptual designer in the aerodynamic panel code, with a pseudo-steady slipstream model wherein rotational effects are discretized onto vortex particle point elements. The method maintains a freedom from volume grids that are so often necessary in the existing interference models. In addition to the lack of a volume grid, the relative computational simplicity allows the aircraft designer the freedom to rapidly test radically different configurations, including more unconventional designs like the channel wing, thereby providing a much broader design space than otherwise possible.Throughout the course of the research, verification and validation studies were conducted to ensure the most accurate model possible was being applied. Once the vortex particle scheme had been verified, and the ability to model an actuator disk with vortex particles had been validated, the overall product was compared against propeller-wing wind tunnel results conducted specifically as benchmarks for numerical methods.The method discussed in this work provides a glimpse into the possibility of pseudo-steady interference modeling using vortex particles. A great groundwork has been laid that already provides reasonable results, and many areas of interest have been discovered where future work could improve the method further. The current state of the method is demonstrated through simulations of several configurations including a wing and nacelle and a channel wing. iv ACKNOWLEDGMENTS My tenure at

show abstract

Analysis of propeller-induced aerodynamic effects

Cited by 11 publications

References 8 publications

Numerical analysis of aerodynamic characteristics for the design of a small ducted fan aircraft

Numerical analysis of aerodynamic characteristics for the design of a small ducted fan aircraft

Unsteady Aerodynamic Investigation of the Propeller-Wing Interaction for a Rocket Launched Unmanned Air Vehicle

A Three Dimensional Vortex Particle-Panel Code For Modeling Propeller-Airframe Interaction

Contact Info

Product

Resources

About