Aerodynamic performance analysis of a supercritical airfoil in the helicopter main rotor

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

doi:10.1139/tcsme-2021-0067

Cited by 5 publications

(5 citation statements)

References 28 publications

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“…Parameters required for computational fluid dynamics simulations are itemized in Table 2. [29,30]. Simulations are used to study the downstream movement of fluids on different wing models.…”

Section: Results and Analysismentioning

confidence: 99%

Streamline Effect Improvement of Additive Manufactured Airfoil Utilizing Dynamic Stream Control Procedure

Srinath

Mukesh²,

Poojari

et al. 2022

Advances in Materials Science and Engineering

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In the era of fast transport, to create inventive stream ow management solutions that are capable of diminishing the aerodynamic drag of the vehicles, there is a need to modify the ow characteristics over the vehicle by deferring or expelling the position of the ow partition. e objective of this study involves the parameterized design of an airfoil utilizing the Bezier curve technique with the assistance of the simulation program. For ow regulations, synthetic jet modules are ingrained at di erent percentages of the chord to manage the stall characteristics. e parametrization system, combined with the stream control method, can give a much better insight into ow re-energization and pave some way for the reduction of the wake. Digital fabrication technique (3d printing or Rapid Prototyping method) is used to fabricate the end product for aerodynamic testing. e comparative outcome showed a reduction in drag at certain angles of attack due to the surface nish obtained. By comparing the results, the aerodynamic e ciency showed a signi cant rise of 13.05% at lower angles of attack when compressed gas was used in the synthetic jet closer to the frontier edge of the airfoil. Near the stall angle of attack, the coe cient of lift (Cl) and coe cient of drag (Cd) values showed no progress.

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Section: Results and Analysismentioning

confidence: 99%

Streamline Effect Improvement of Additive Manufactured Airfoil Utilizing Dynamic Stream Control Procedure

Srinath

Mukesh²,

Poojari

et al. 2022

Advances in Materials Science and Engineering

Self Cite

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“…Advancements in additive manufacturing technologies help many fields in engineering, medicine, and research to test or demonstrate the models [14,15]. Material qualities are improved by the advancements in the development of composite materials and help make low-cost models faster [16].…”

Section: Introductionmentioning

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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“…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]. A lot of innovative designs alter the geometry of the airfoil used to get high lift during takeoff and landing.…”

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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Aerodynamic performance analysis of a supercritical airfoil in the helicopter main rotor

Cited by 5 publications

References 28 publications

Streamline Effect Improvement of Additive Manufactured Airfoil Utilizing Dynamic Stream Control Procedure

Streamline Effect Improvement of Additive Manufactured Airfoil Utilizing Dynamic Stream Control Procedure

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

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

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