Author
Alexander Kusyumov
Bio: Alexander Kusyumov is an academic researcher. The author has contributed to research in topics: Fuselage & Aerodynamics. The author has an hindex of 1, co-authored 1 publications receiving 10 citations.
Topics: Fuselage, Aerodynamics, Helicopter rotor, Drag
Papers
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Journal Article•
TL;DR: In this paper, the aerodynamic lift and drag of the ANSAT helicopter fuselage prototypes using Computational Fluid Dynamics (CFLD) was investigated under the assumption of steady flow conditions.
Abstract: This paper investigates the aerodynamic lift and drag of the ANSAT helicopter fuselage prototypes using Computational Fluid Dynamics. The CAD model of the fuselage was meshed using an unstructured grid and computed using a viscous flow model under the assumption of steady flow conditions. To account for the influence of the helicopter rotor an actuator disk model was used and the results were compared with computations for the isolated fuselage. The contributions to the total drag of the individual helicopter fuselage components were also studied using different turbulence models. The key components of the fuselage drag were identified.
10 citations
Cited by
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TL;DR: The demonstrated method can be applied to fuselages of any shape during the initial design phase and is shown that a decrease of fuselage drag around 2.5% is possible without compromising the structure and the functionality of the design.
26 citations
TL;DR: In this article, two numerical methods: Reynolds-Averaged Navier-Stokes (RANS) and a hybrid RANS-LES method: improved delayed detached-eddy simulation (IDDES) method are performed for the simulation of a prototype helicopter fuselage.
12 citations
TL;DR: In this paper, the authors present aerodynamic analyses of realistic fuselage configurations using computational fluid dynamics using a development model of the Ansat helicopter, and further modifications are introduced to the fuselage model to demonstrate drag reduction via small shape changes.
Abstract: The aim of this paper is to present aerodynamic analyses of realistic fuselage configurations using computational fluid dynamics. A development model of the Ansat helicopter is employed. The model is tested at the subsonic wind tunnel of the Kazan National Research Technical University/Kazan Aviation Institute for a range of Reynolds numbers, pitch, and yaw angles. The computational fluid dynamics results were found to be in fair agreement with the test data and revealed flow separation at the rear of the fuselage. Once confidence in the computational fluid dynamics method was established, further modifications were introduced to the fuselage model to demonstrate drag reduction via small shape changes. The contribution to the overall drag from each fuselage part and the interference drag between the main fuselage components were also investigated.
10 citations
TL;DR: In this paper, fully-resolved rotor-fuselage interactional aerodynamics is used as the forcing term in a model based on the Euler-Bernoulli equation, aiming to simulate helicopter tail-boom vibration.
Abstract: In this work, fully-resolved rotor-fuselage interactional aerodynamics is used as the forcing term in a model based on the Euler-Bernoulli equation, aiming to simulate helicopter tail-boom vibration. The model is based on linear beam analysis and captures the effect of the blade-passing as well as the effect of the changing force direction on the boom. The Computational Fluid Dynamics (CFD) results were obtained using a well-validated helicopter simulation tool. Results for the tail-boom vibration are not validated due to lack of experimental data, but were obtained using an established analytical approach and serve to demonstrate the strong effect of aerodynamics on tail-boom aeroelastic behavior.
5 citations