Experimental investigation of the effect of yaw angle on the inflow of a two-bladed propeller

Zarev, Angel; Green, Richard

doi:10.1016/j.ast.2020.105940

Cited by 6 publications

(3 citation statements)

References 20 publications

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“…The k − ω turbulence model has been proven over a variety of validation investigations to provide both accuracy and efficiency. These investigations using HMB3 have included propeller flow validation in both installed and isolated conditions, by comparison with the experimental results of the Joint Open Rotor Propeller (JORP) blade [23], the Improving the Propulsion Aerodynamic and aCoustics of Turboprop Aircraft (IMPACTA) wind tunnel tests [24,25] and the model aircraft propeller inflow investigation at the University of Glasgow [26].…”

Section: Methodsmentioning

confidence: 99%

A computational fluid dynamic acoustic investigation of a tiltwing eVTOL concept aircraft

Higgins

Barakos

Shahpar

et al. 2021

Aerospace Science and Technology

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Section: Methodsmentioning

confidence: 99%

A computational fluid dynamic acoustic investigation of a tiltwing eVTOL concept aircraft

Higgins

Barakos

Shahpar

et al. 2021

Aerospace Science and Technology

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“…Theys et al [7] conducted wind tunnel tests on a small rotor blade of a UAV to investigate the changes in propeller torque under different operating conditions. Zarev and Green [8] performed an experimental investigation to measure the inflow of a two-bladed propeller. The research was conducted over a range of advance ratios (J = 0.36 to 1.54) and yaw angles (γ = 0 to 20 • ) at a Reynolds number of Re ≈ 111,000, based on the chord length and advancing blade resultant velocity at the 70% spanwise position.…”

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

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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.

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“…Amir 9 and Theys 10 conducted experiments on the small-scale rotor for UAV through tilt angles from 0 to 180° to investigate the variations of yaw moment at different operating conditions. Angel 11 used the Laser Doppler Anemometry (LDA) system to capture the propeller’s inflow in yaw.…”

Section: Introductionmentioning

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:

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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.

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Experimental investigation of the effect of yaw angle on the inflow of a two-bladed propeller

Cited by 6 publications

References 20 publications

A computational fluid dynamic acoustic investigation of a tiltwing eVTOL concept aircraft

A computational fluid dynamic acoustic investigation of a tiltwing eVTOL concept aircraft

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

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

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