Detailed Aerodynamic Analysis of a Shrouded Tail Rotor Using an Unstructured Mesh Flow Solver

Lee, Hee Dong; Kwon, Oh Joon

doi:10.2322/tjsass.47.23

Cited by 6 publications

(2 citation statements)

References 7 publications

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“…To the validation of the CFD and momentum-element model, the induced velocity at the rotor disk fits with the test values at a splendid level. The comparison error between CFD calculation and test values in the relevant research and the cross-validation error between the rotor's momentum-element model and CFD are both about 0.1 [21] as shown in Figure 10 and Table 3. This indicates that the CFD method and the momentum-element model are credible and reasonable.…”

Section: Design Goalmentioning

confidence: 95%

The Overall Design of Variable Diameter Ducted Fan in the Aircraft

Gao¹,

Xu²

2022

Aerospace

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Variable diameter rotor can improve the flight performance of the aircraft both in hovering and forward flying and a duct can improve the rotor performance further both in force and efficiency. In previous studies, those two parts are always studied in the one-factor-at-a-time method, and the duct is lack diameter change so that it cannot cooperate with the variable diameter rotor. In this paper, the Chinese utility helicopter Z9 is taken as the prototype, and the structural parameters of the variable diameter ducted fan (VDDF) are selected by an orthogonal experiment method. Based on the momentum-element theory, the aerodynamic theoretical model of the disk is established, and the structural parameters that can achieve the best efficiency in hover/propulsion and the best lift/thrust force ratio under different modes are obtained in the orthogonal range by computational fluid dynamics method. The structural parameters of the VDDF under the set working conditions are obtained by a technique for order of preference by similarity to ideal solution (TOPSIS) evaluation and the flight performance of the aircraft equipped with the VDDF is superior to the prototype: The max takeoff weight raises 25%; the hover ceiling raises 90%; the cruise altitude raises 11%; the cruise speed raises 23% and the max speed raises further. However, a better engine may be needed to provide greater power.

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Section: Design Goalmentioning

confidence: 95%

The Overall Design of Variable Diameter Ducted Fan in the Aircraft

Gao¹,

Xu²

2022

Aerospace

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“…At this moment, the predicted thrust from the present calculation is 9.547 kg. The rotor thrust in [28] and [29] are 9.54 kg and 9.69 kg, respectively. The coincidence indicates that our method can investigate aerodynamic performance of ducted tail rotor effectively.…”

Section: Aerodynamic Performance Of the Ducted Tailmentioning

confidence: 99%

Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method

Wang

et al. 2017

Mathematical Problems in Engineering

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A detailed aerodynamic performance of a ducted tail rotor in hover has been numerically studied using CFD technique. The general governing equations of turbulent flow around ducted tail rotor are given and directly solved by using finite volume discretization and Runge-Kutta time integration. The calculations of the lift characteristics of the ducted tail rotor can be obtained. In order to predict the aerodynamic noise, a hybrid method combining computational aeroacoustic with boundary element method (BEM) has been proposed. The computational steps include the following: firstly, the unsteady flow around rotor is calculated using the CFD method to get the noise source information; secondly, the radiate sound pressure is calculated using the acoustic analogy Curle equation in the frequency domain; lastly, the scattering effect of the duct wall on the propagation of the sound wave is presented using an acoustic thin-body BEM. The aerodynamic results and the calculated sound pressure levels are compared with the known technique for validation. The sound pressure directivity and scattering effect are shown to demonstrate the validity and applicability of the method.

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Numerical investigation on the hovering performance of contra-rotating ducted rotor for micro air vehicle

Lee

Kim²

2020

Microsyst Technol

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Detailed Aerodynamic Analysis of a Shrouded Tail Rotor Using an Unstructured Mesh Flow Solver

Cited by 6 publications

References 7 publications

The Overall Design of Variable Diameter Ducted Fan in the Aircraft

The Overall Design of Variable Diameter Ducted Fan in the Aircraft

Computation of Aerodynamic Noise Radiated from Ducted Tail Rotor Using Boundary Element Method

Numerical investigation on the hovering performance of contra-rotating ducted rotor for micro air vehicle

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