Integration of Airfoil Stall and Compressibility Models into a Propeller Blade Element Model

Dorfling, Johann; Rokhsaz, Kamran

doi:10.1061/(asce)as.1943-5525.0000607

Cited by 6 publications

(5 citation statements)

References 27 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…These are created using XFOIL, 25 based on the NACA 64A416 blade section. 26 The lift and drag coefficients are then corrected for three-dimensional 27 and compressibility 28 (valid up to Mach number 0.9) effects, and hub and tip loss factors 29 are applied. Subsequently, propeller performance parameters such as thrust, torque, and efficiency can be determined by integrating the forces acting on the blade elements.…”

Section: Iiib Blade Element Modelmentioning

confidence: 99%

Aerodynamic Investigation of an Over-the-Wing Propeller for Distributed Propulsion

Marcus

Vries

Kulkarni

et al. 2018

2018 AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

This paper addresses the aerodynamic performance and numerical modeling of overthe-wing propellers. Installing the propeller above a wing has the potential to increase wing lift-to-drag ratio, high-lift capabilities, and to reduce flyover noise. However, the prediction of its performance is difficult, since research on the aerodynamic interaction effects of over-the-wing propellers has been limited so far. For this reason, an exploratory wind tunnel campaign was performed with a wing featuring a fowler flap. A single propeller was installed above the wing at different chordwise locations and inclination angles. Wing surface-pressure and wake-pressure measurements showed strong, bilateral aerodynamic coupling between the propeller and wing. A configuration with the propeller attached to the flap showed wing lift increases of 8% and 3% in cruise and high-lift conditions, respectively. The key findings of the wind tunnel campaign were used to validate a low-fidelity numerical tool, which combines a non-uniform inflow blade-element model for the propeller, a panel method for the wing, and a vortex lattice model for the propeller slipstream. The numerical model was used to assess the effect of propeller axial location and diameter. Results indicated that the optimal axial propeller position is near the trailing edge of the wing, and that reducing the propeller diameter at constant thrust coefficient at this location is beneficial for distributed propulsion applications. The tool allows a rapid computation of over-the-wing propeller and wing performance in cruise conditions. This enables an efficient design space exploration during the conceptual design process of such configurations.

show abstract

Section: Iiib Blade Element Modelmentioning

confidence: 99%

Aerodynamic Investigation of an Over-the-Wing Propeller for Distributed Propulsion

Marcus

Vries

Kulkarni

et al. 2018

2018 AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

show abstract

“…This model has been reportedly validated by experiments presented in Ref. 25. As shown in equation (16), this correction model describes the correction factor as a function of Mach number M ∞ , thickness-to-chord ratio t/c, and heat capacity ratio γ .…”

Section: Bet Correction Modelmentioning

confidence: 78%

“…However, it usually fails to converge due to this correction model. Instead, a relatively simple but effective Mach correction method called ‘Dorfling’s compressibility correction’ 25 is incorporated in this BET model to ensure the stability of the model. This model has been reportedly validated by experiments presented in Ref.…”

Section: Bet Correction Modelmentioning

confidence: 99%

Modelling, analysis and experimental study of the prop-rotor of vertical/short-take-off and landing aircraft

Yang

Wang

Zhu

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The main objective of this work is to characterise the prop-rotor of V/STOL (Vertical/short-take-off and landing) aircraft in various operating conditions, especially in transition flight. To this end, a BET (Blade element theory) based analytic model/tool with a low computational cost has been built to predict the aerodynamic performance of the prop-rotor. This BET-based model can predict prop-rotor thrust, torque, normal force, and yaw moment as well as their corresponding 1P load (once-per-revolution load on the single blade) regarding oblique flow. This model is verified and shows good consistency with the wind tunnel experimental data and CFD simulation results. Furthermore, by using this BET model/tool, the effects of axial advance ratio, tilt angle and collective pitch angle on these component loads on the prop-rotor are explored. Moreover, the effects of these variables on the vibratory amplitudes of the 1P load on the single blade and 3P harmonic loads on the prop-rotor due to inclined flow are presented as well.

show abstract

“…Kim et al [4] developed a propeller model to predict isolated propeller performances under steady flight conditions, in which the vortex lattice method was used to compute the induced velocities while the strip theory was employed to calculate the forces and moments produced by the propeller. Dorfling et al [5] developed a nonlinear aerodynamic model of the airfoil that can be used in conjunction with the blade element method to enhance the prediction of propeller performance over a wide range of forward ratios. Kolaei et al [6] studied the performance characteristics of a rotor, typically used in small unmanned aerial vehicles (UAVs), in a series of wind tunnel tests for a wide range of advance ratios and inflow angles.…”

Section: Introductionmentioning

confidence: 99%

Research on the Calculation Method of Propeller 1P Loads Based on the Blade Element Momentum Theory

Yan,

Tian,

Zhou

et al. 2024

Aerospace

View full text Add to dashboard Cite

Aircraft propellers produce relatively large in-plane loads, called propeller 1P loads, during maneuvers such as turning, diving, and lifting, and these loads can negatively affect the flight and control of the aircraft. In order to study the change rule of 1P aerodynamic loads, in this paper, a mathematical model of the propeller 1P aerodynamic loads has been developed based on the blade element momentum theory. This mathematical model was then corrected using the Pitt–Peters incoming flow correction method, the Prandtl tip correction method, and the propeller root flow correction method. Based on this mathematical model, a calculation procedure for the propeller 1P aerodynamic loads was developed using MATLAB software, and the accuracy of the procedure was verified by comparing the results with CFD simulation results. Numerical simulations show that the results calculated based on the proposed mathematical model for the coefficients of thrust, power, bending moment, and the tangential force of the propeller have an error of less than ±6.00% compared to the CFD simulation results. For a small inflow angle, the coefficients of bending moment and tangential force of the whole propeller fluctuate in a small range. But, as the inflow angle increases, the fluctuation range of the aerodynamic characteristic parameters of the propeller increases and the fluctuation becomes more complicated. Through numerical calculations, it has been shown that the mathematical model presented herein is reliable and accurate. In addition, it greatly shortens the calculation time and improves the calculation efficiency. It is expected that the proposed model can provide a certain help for the strength design of the propeller structure and the study of the aerodynamic performance of the whole aircraft.

show abstract

Integration of Airfoil Stall and Compressibility Models into a Propeller Blade Element Model

Cited by 6 publications

References 27 publications

Aerodynamic Investigation of an Over-the-Wing Propeller for Distributed Propulsion

Aerodynamic Investigation of an Over-the-Wing Propeller for Distributed Propulsion

Modelling, analysis and experimental study of the prop-rotor of vertical/short-take-off and landing aircraft

Research on the Calculation Method of Propeller 1P Loads Based on the Blade Element Momentum Theory

Contact Info

Product

Resources

About