Design and Numerical Simulation of Convergent Divergent Nozzle

Ramji, V.; Mukesh, R.; Hasan, Inamul

doi:10.4028/www.scientific.net/amm.852.617

Cited by 7 publications

(5 citation statements)

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“…The drag coefficient is used to denote the rearward force that disturbs the airflow of an airfoil 1. As per the result mentioned in Table 4, a stall occurs at a 14° AOA, and the maximum lift occurs at a 12° AOA (Piedra et al, 2018;Ramji et al, 2016).…”

Section: Cfd Resultssupporting

confidence: 64%

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

2024

JST

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This study represents the aerodynamic design of an Unmanned aerial vehicle intended for surveillance or agriculture with a maximum take weight of 125 kg. Weight estimation and constraint analysis were done based on the Mission profile. Design of Computer-Aided Design (CAD) models were generated for three different configurations using CATIA V5R20 as a high wing, mid-wing, and low wing. Flow analysis was done for the above configurations at various angles of attack. ANSYS 15 was used for the flow Analysis. A Tetrahedron element meshed the model with the minimum required orthogonal quality. Five microns were given to the initial layer height of the prism mesh. Spalart Allmaras model is used as the Turbulence model in the solver. The aerodynamic characteristics of the above configuration obtained from Computational Fluid Dynamics (CFD) results were compared with the DATCOM program and validated with the wind tunnel experimental test data. The open-circuited suction-type Subsonic wind tunnel was employed for the test. The aerodynamic properties for the angle of attack in the range of -2° to 14° angle of attack are calculated using a six-component balance.The study aims to find the Unmanned Aerial Vehicle (UAV) configuration based on the aerodynamic characteristics obtained from the CFD and DATCOM results. High-wing UAVs have better aerodynamic efficiency than the other two configurations.

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Section: Cfd Resultssupporting

confidence: 64%

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

2024

JST

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“…The adaptive dropped hinge flap was one of the designs which are better than the conventional Fowler flap [22]. High-lift devices usually increase the size of the flight envelope by altering the structure of the wing section [23]. NACA 6412 airfoil series has been widely used for aerodynamic analysis from the olden days to modern days since its applications in low-speed aerodynamics [9,24].…”

Section: Review Of Literature and Theorymentioning

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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“…The turbulent kinetic energy (k) and dissipation rate (ε) are the fundamental parameters of nozzle flow modelling where the flow has higher Reynolds number. The combination of turbulence model Spalart-Allmaras and Standard k-ε were applied by Ramji and Hasan [16], to analyse the minimum length of the divergent section for various Ma in supersonic and hypersonic nozzle. In addition, they were used to plot the graph of static pressure and Ma on the centreline and near the wall as was conducted by Kiran et al, [17].…”

Section: Introductionmentioning

confidence: 99%

A New Modified k-ɛ Turbulence Model for Predicting Compressible Flow in Non- Symmetrical Planar-Curvature Converging-Diverging Supersonic Nozzle

Pujowidodor¹,

Siswantara²,

Budiarso³

et al. 2020

CFDL

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Convergent-Divergent (CD) nozzle of a compressible fluid is a common device to accelerate fluid flow to a higher supersonic speed and to direct or modify the fluid flow. CD nozzle has been applied in wide range of fluid equipment such as turbine power, chemical mixing equipment, turbojet engine, and rocket. The performance of CD nozzle is strongly affected by its geometry at certain pressure ratio and the flow characteristic. In the case of complicated flow phenomena within a supersonic flow, especially in the turbulence flow, many studies use the computational simulation to obtain the detailed behavior and properties of flow. However, the k-epsilon turbulence model has limitations in predicting the effect of dissipation due to the viscous friction. This study aims to propose the new modified k-ε turbulence model in planar-curvature Convergent-Divergent (CD) nozzle of a compressible fluid. Two equations model of modified Standard k-ε for predicting the compressible flow within planar-curvature CD nozzle was discussed. The simulation model was run in 2D and steady, while fluid was assumed as an ideal gas with domain size was 0.65 m length, 0.071 m width. In addition, it has been discretized in 3510 structured independent grid cells. The results depicted that in the divergent section of the nozzle (supersonic region), the fluid expansion caused the change in fluid parameters such as time-average of pressure, temperature, density, and velocity. This study found that the expanded cross-sectional area with non-symmetrical planar curvature affected the turbulence behavior and properties. Furthermore, the new modified constants of c2 in dissipation equation and cμ of eddy viscosity model could give a better prediction than the original constant of the k-ε turbulence model.

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Design and Numerical Simulation of Convergent Divergent Nozzle

Cited by 7 publications

References 0 publications

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

Energy Industry and Industrial Design (Innovations in Energy Utilization and Equipment Design)

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

A New Modified k-ɛ Turbulence Model for Predicting Compressible Flow in Non- Symmetrical Planar-Curvature Converging-Diverging Supersonic Nozzle

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