Wind Tunnel Simulation of Propeller Effects in the A400M FLA-4 Model

Müller, Jürg; Aschwanden, Marianne; Plaza, Guzman de Andres; Fuente, Jorge García de la; Jimenez, Oscar Pires

doi:10.2514/6.2005-3706

Cited by 5 publications

(5 citation statements)

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“…More details of the test can be found in Ref. 7. The 1P loads and moments are typically presented in terms of a total 1P force or moment plus a lag angle referred to the z-axis (positive lag according to the sense of rotation of the propeller).…”

Section: Uninstalled Propeller Resultsmentioning

confidence: 99%

CFD computation of in-plane propeller shaft loads

Ruiz-Calavera

Perdones-Diaz

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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A study has been performed to analyze the feasibility of predicting in-plane shaft loads (so-called 1P loads) of installed propellers using CFD. The A400M military transport aircraft has been used as case study. The results of the computations are compared to both wind tunnel and flight test data. For the flight test comparison the effect of propeller flexibility has been taken into account by means of a coupled CFD-CSM analysis. Nomenclature B 1P= 1P shaft bending moment C B1P = 1P shaft bending moment coefficient = B 1P /( n 2 D 5 )= 1P propeller moment n = propeller rotational speed (rps) = air density

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Section: Uninstalled Propeller Resultsmentioning

confidence: 99%

CFD computation of in-plane propeller shaft loads

Ruiz-Calavera

Perdones-Diaz

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…During the experiment by Gamble et al, a static test bench was built to characterize the forces and moments acting on the motor and on a micro air vehicle, in which the influence of axial and vertical wing placements on propeller and wing loads was collected [16]. As observed from the wind tunnel experiments of Airbus A400M military transport aircraft [17], four 6-component Rotating Shaft Balances were used to measure the thrust and torque plus the forces and moments contained in the propeller rotating plane (so called 1P-force). In addition, Garofano et al [18] and Yang et al [19] applied the 6-component balance to the ground effect experiment and aeroacoustics experiment of the propeller, which indicated that the balance provided an effective way to understand the aerodynamic characteristics of various configurations of propellers.…”

Section: Introductionmentioning

confidence: 99%

An Experimental and Numerical Evaluation of the Aerodynamic Performance of a UAV Propeller Considering Pitch Motion

Zhang

Xie

Wang

et al. 2023

Drones

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Considering the vibration generated by a propeller-driven UAV or encountering gust, the propeller will perform a very complex follower motion. A pitch and rotating coupled motion is proposed in the present work that can take more complex unsteady performance of follower force than a regular fixed-point rotating motion. In order to evaluate the unsteady follower force and conduct parametric study, an extensive ground test bench was designed for this purpose where the whole test system was driven by a linear servo actuator and the follower force was measured by a 6-component balance. For CFD simulation, coupled motion in particular needs detailed unsteady aerodynamic model; therefore, a high-fidelity CFD-based study integrated with the overset mesh method was complemented to solve the unsteady fluid of varying conditions. The results suggest that a significant influence on unsteady follower force is observed, and the mean value of in-plane force does not equal to zero during the coupled motion process. Compared with the regular fixed-point rotation of propeller, the fluctuation frequency of follower force in present work couples the rotation and pitch motion frequencies. In addition, the oscillation amplitude of out-plane force and torque is positively related with the pitch frequency, pitch amplitude, and relative length from leading edge of wing to the rotation center. For example, the oscillation amplitude of 1-blade’s out-plane force and torque increases by 57.122% and 66.542% for the 5 Hz-5 deg case compared with the 5 Hz-3 deg case, respectively. However, the torque is not sensitive to frequency of pitch motion. The generally excellent agreement evident between the ground test and numerical simulation results is important as guidance for our future investigation on “dynamic” aerodynamic performance of a propeller-driven UAV.

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“…Such as the European Airbus A400 transport aircraft and the U.S. C-130 "Hercules" transport aircraft and Predator series of UAV (shown as fig.1) [1][2],as well as domestic MA60, YUN7, YUN8, YUN12 transport aircraft and so on [3], are all using turboprop propulsion systems. In the development process of propeller aircraft aerodynamic design must take into consideration on the aerodynamic performance of the propeller slipstream interference on the configuration .This interference is more prominent than the slipstream affect of turbojet, even can determine the success of the entire aircraft design .So it is very important to carry out research of the aircraft propeller slipstream aerodynamic interference .Propeller slipstream aircraft interference assessment has been one of the difficulties of propeller aircraft aerodynamic design [4][5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation Study on Propeller Slipstream Interference of High Altitude Long Endurance Unmanned Air Vehicle

Chen

et al. 2015

Procedia Engineering

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In this paper ,the control equation of Multiple Reference Frame(MRF) as the propeller calculation model was present and analyzed, the propeller slipstream interference on HALE UAV was studied with three-dimensional numerical simulation. It is shown that the flow field of the MRF model is good consistent with true propeller flow, and MRF can accurately simulate aerodynamic interference on the aircraft. The stream traces on the V-tail surface were deflected and shrank, pressure distribution ,Cmx and Cmz on V-tail surface was changed apparently too.But slipstream had little effect on wing. The influence of propeller slipstream on the aerodynamic performance of the UAV at the status of taking off is biggest, become weaker at status of climbing and smallest at the status of cruising. The influence of propeller slipstream is enhanced with increment of propeller thrust and basically familiar in the same thrust between the two blade attack angle. The pressure drag on aft of UAV fuselage increased rapidly by the interference of propeller slipstream, leading aerodynamic performance of UAV become badly.

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Wind Tunnel Simulation of Propeller Effects in the A400M FLA-4 Model

Cited by 5 publications

References 0 publications

CFD computation of in-plane propeller shaft loads

CFD computation of in-plane propeller shaft loads

An Experimental and Numerical Evaluation of the Aerodynamic Performance of a UAV Propeller Considering Pitch Motion

Numerical Simulation Study on Propeller Slipstream Interference of High Altitude Long Endurance Unmanned Air Vehicle

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