Forward Flight Performance Analysis of Supercritical Airfoil in Helicopter Main Rotor

Hasan, Inamul; Mukesh, R.; Krishnan, P. Radha; Srinath, R.; Prakash, R.

doi:10.32604/iasc.2022.023252

Cited by 7 publications

(4 citation statements)

References 28 publications

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“…Catia V5 is used in this research work to design the three-bladed and four-bladed helicopter blades. e same model is used for the experimental model and scaled down for wind tunnel size using the 3D printing method [19,20]. e designed model will be imported to fluent for further analysis.…”

Section: Design and Preprocessingmentioning

confidence: 99%

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

Hasan

Mukesh²,

Krishnan

et al. 2022

Advances in Materials Science and Engineering

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This research paper aims to validate the aerodynamic performance of rotor blades using additive manufacturing techniques. Wind tunnel testing is a technique used to find the flow characteristics of the body. Computational fluid dynamics (CFD) techniques are used for aerodynamic analysis, and validation should be done using wind tunnel testing. In the aerodynamic testing of models, additive manufacturing techniques help in validating the results by making models easily for wind tunnels. Recent developments in additive manufacturing help in the aerodynamic testing of models in wind tunnels. The CFD analysis of helicopter rotor blades was analyzed in this research, and validation was done using additive manufacturing techniques. Computational analysis was carried out for static analysis for the forward speeds of Mach numbers 0.3, 0.4, and 0.5. The results obtained were satisfactory to the previous results and were validated with wind tunnel testing. Results proved that the error percentage was lower, and the computational analysis was valid. In this research, models were designed using the FDM technique for wind tunnel testing as it is cost-effective and easy to manufacture.

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Section: Design and Preprocessingmentioning

confidence: 99%

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

Hasan

Mukesh²,

Krishnan

et al. 2022

Advances in Materials Science and Engineering

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“…And unstructured meshing can also be used for wing (3D) analysis [19]. There is a lot of evidence for the increment in the lift with respect to the high angle of attack, and flow over an airfoil separates when the velocity of the flow around the airfoil is less [20]. To do the computational analysis for the nozzles, Ansys Fluent and CFD solvers are used, and K-ε model, K-omega, and Spalart Allmaras model are used as turbulence models [21].…”

Section: Review Of Literature and Theorymentioning

confidence: 99%

“…Using the k-ω model in the interior parts of the boundary layer causes the model to use directly down to the wall through the viscous sublayer, so the shear stress transport (SST) k-ω model can be used as a low Reynolds turbulence model without any additional damping functions. The SST modal also changes to a k-epsilon (ε) behaviour in the free stream[20,21,25]. Therefore, it avoids the general k-ω problem that the model is highly sensitive to the inlet turbulence properties of the free stream.…”

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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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“…Wang (Wang et al , 2023) and Li (Li et al , 2021) conducted a study of the dynamic stall of the S809 airfoil in a sandy environment. Hasan (Hasan et al , 2022b; Hasan and P, 2022a) studied the influence of supercritical airfoil on helicopter characteristics and found that supercritical airfoil can increase efficiency and produce good aerodynamic characteristics. Liu (Liu et al , 2023) analysed the effect of sandy flow with a low Reynolds number in transonic flow on the aerodynamic performance of an airfoil of a Mars UAV.…”

Section: Introductionmentioning

confidence: 99%

Helicopter airfoil aerodynamic characteristics and rotor trim in sandy environments

Huang,

Cao,

Wang

2024

AEAT

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Purpose The sandy environment is one of the typical environments in which helicopters operate. Air-sand two-phase flow in sandy environments may be an important factor affecting flight safety. Taking a typical example, this paper aims to investigate the aerodynamic and rotor trim characteristics of the UH-60 helicopter in sandy environments. Design/methodology/approach A computational study is conducted to simulate the air-sand flow over airfoils based on the Euler–Lagrange framework. The simulation uses the S-A turbulence model and the two-way momentum coupling methodology. Additionally, the trim characteristics of the UH-60 rotor are calculated based on the isolated rotor trim algorithm. Findings The simulation results show that air-sand flow significantly affects the aerodynamic characteristics of the SC1095 airfoil and the SC1094R8 airfoil. The presence of sand particles leads to a decrease in lift and an increase in drag. The calculation results of the UH-60 helicopter rotor indicate that the thrust decreases and the torque increases in the sandy environment. To maintain a steady forward flight in sandy environments, it is necessary to increase the collective pitch and the longitudinal cyclic pitch. Originality/value In this paper, the aerodynamic characteristics of airfoils and the trim characteristics in the air-sand flow of the UH-60 helicopter are discussed, which might be a new view to analyse the impact of sandy environments on helicopter safety and manoeuvring.

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Forward Flight Performance Analysis of Supercritical Airfoil in Helicopter Main Rotor

Cited by 7 publications

References 28 publications

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

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

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

Helicopter airfoil aerodynamic characteristics and rotor trim in sandy environments

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