Wind Tunnel Testing and Validation of Helicopter Rotor Blades Using Additive Manufacturing

Hasan, Inamul; Mukesh, R.; Krishnan, P. Radha; Srinath, R.; Babu, Dhanya Prakash; Gurmu, Negash Lemma

doi:10.1155/2022/4052208

Cited by 4 publications

(5 citation statements)

References 30 publications

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Section: Validation Of the Numerical Approach And Experimental Approachmentioning

confidence: 99%

“…The analysis showed that the CFD results slightly overestimated the experimental data obtained from the wind tunnel, with an average error of 10%. However, based on the criteria recommended in [32], it was deemed that the validation of the CFD modeling study was acceptable. The numerical approach employed in this study validates that forward flight conditions create a scenario where the lift force appreciably surpasses that in hover cases by an average of 39.9%.…”

Section: Validation Of the Numerical Approach And Experimental Approachmentioning

confidence: 99%

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Investigating and Analyzing the Potential for Regenerating Excess Energy in a Helicopter UAV

Kodchaniphaphong,

Pukrushpan,

Klumpol

2023

Drones

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Energy consumption is a critical parameter in the development of helicopter Unmanned Aerial Vehicles (UAVs). Today, helicopter UAVs are playing an increasingly pivotal role in various applications, from surveillance and reconnaissance to package delivery and search and rescue missions. However, their energy efficiency remains a pressing issue, as it directly impacts their operational duration and payload capacity. One of the key challenges in optimizing energy consumption is the existence of excess power during flight, arising from the intricate interplay between helicopter aerodynamic behavior and safety design. Typically, this excess energy is dissipated, resulting in a suboptimal performance and efficiency. This study investigated the behavior of excess power in a helicopter Unmanned Aerial Vehicle (UAV). Typically, this excess energy is wasted in conventional helicopters and helicopter UAVs. A dual-method approach, encompassing numerical and experimental methodologies, was employed to provide comprehensive insights into the helicopter UAV’s performance under various conditions. Computational fluid dynamics (CFD) simulations were performed to analyze the UAV’s aerodynamics. The simulations were validated by comparing the lift force with wind tunnel experimental data, resulting in acceptable deviations. The experimental analysis was conducted using a wind tunnel and a small-sized helicopter UAV. The experiments were designed to examine the excess power behavior of the UAV under two distinct flight conditions: hover and forward flight. The power output from the generator and power input from the battery were measured under various angular velocities and pitch angles. The results revealed a maximum excess power of 6.84% for hover conditions and 9.83% for forward flight conditions. This indicates that the maximum excess power percentage attributable to the helicopter UAV’s safety measure is 6.84% and that resulting from aerodynamics is 2.99%. The findings of this study contribute valuable knowledge to the optimization of helicopter UAV performance and the potential for harnessing excess power during flight operations. When this excess energy is harnessed, it can contribute significantly to the overall performance and efficiency of the UAV, potentially extending its flight duration or accommodating additional payload capacity that could potentially pave the way for the development of hybrid helicopter UAV models in the future.

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Section: Validation Of the Numerical Approach And Experimental Approachmentioning

confidence: 99%

Section: Validation Of the Numerical Approach And Experimental Approachmentioning

confidence: 99%

Investigating and Analyzing the Potential for Regenerating Excess Energy in a Helicopter UAV

Kodchaniphaphong,

Pukrushpan,

Klumpol

2023

Drones

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“…The difference between these equations' successive solutions will be shown by the residual plot. In a CFD simulation, the residual measures the local imbalance of the conserved variable in each control volume [36][37][38]. Therefore, the wing model will have its particular residual value for every equation solved in each cell.…”

Section: Study Of Rectangular Wing Model Using Naca 6412 Airfoilmentioning

confidence: 99%

“…Therefore, it avoids the general k-ω problem that the model is highly sensitive to the inlet turbulence properties of the free stream. Researchers often merit the SST k-ω model high because of its good behaviour in adverse pressure gradients and separating flows[34][35][36].…”

mentioning

confidence: 99%

Comparative Study and Aerodynamic Analysis of Rectangular Wing Using High-Lift Systems

Krishnan

Mukesh²,

Hasan³

et al. 2023

International Journal of Aerospace Engineering

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High-lift systems are designed to expand the flight envelope and have a most important effect on the size of the wing, economy, and safety of many airliner configurations. Even a small increment of lift using a high-lift system can significantly impact an aircraft’s profitability. The effective design of the airfoil shape with the required aerodynamic performance is still difficult. In the early days, the designs of airfoils were randomly set up and tested in the flow section, and then, the Wright brothers emerged with a cambered section. NACA has provided an appropriate airfoil definition that supports us in making airfoil designs using formulas, not randomly. This paper describes the influence of aerodynamic analysis of wing with flaps at various deflection angles. Aerodynamic variables for the aircraft wing, which is made up of the NACA airfoil 6412 model with and without flaps, have been studied at various angle of attack (AOA) (i.e., -4, -2, 0, 2, 4, 6, 8, 10, 12, and 16) and different Mach number at 0.2, 0.3, and 0.4. Also, the analysis was done for the 15000 ft altitude to check the density effects for the real-time applications. The coefficients of lift and drag are gained by examining the pressure distribution over the surface of the wing. Lift increases as the approach ascends from a low to a high angle of attack, and the most extreme lift is produced at a specific point. After that, when the angle of attack increases further, the drag component increases, so the stall occurs at that point in time. The results showed that the NACA 6412 airfoil obtained the maximum lift at 14°, and the lift value started to decrease. The CFD computations are performed in Ansys Fluent by performing hybrid mesh using ICEM-CFD. The analysis is performed for various configurations of the wing section, and the effects of flow parameters like angle of attack, altitude, and the gap distance between the main wing and slotted flap were compared to identify the better configurations.

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“…Tis article has been retracted by Hindawi, as publisher, following an investigation undertaken by the publisher [1]. Tis investigation has uncovered evidence of systematic manipulation of the publication and peer-review process.…”

mentioning

confidence: 99%

Retracted: Wind Tunnel Testing and Validation of Helicopter Rotor Blades Using Additive Manufacturing

2023

Advances in Materials Science and Engineering

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Wind Tunnel Testing and Validation of Helicopter Rotor Blades Using Additive Manufacturing

Cited by 4 publications

References 30 publications

Investigating and Analyzing the Potential for Regenerating Excess Energy in a Helicopter UAV

Investigating and Analyzing the Potential for Regenerating Excess Energy in a Helicopter UAV

Comparative Study and Aerodynamic Analysis of Rectangular Wing Using High-Lift Systems

Retracted: Wind Tunnel Testing and Validation of Helicopter Rotor Blades Using Additive Manufacturing

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