Vortex Dynamics Analysis of Straight-Body-Type-Fuselage Fighter Using CFD Simulation

Sutrisno, Sutrisno; Deendarlianto, Deendarlianto; Rohmat, Tri Agung; Wibowo, Setyawan Bekti; Iswahyudi, Sigit

doi:10.5028/jatm.v12.1104

Cited by 3 publications

(1 citation statement)

References 23 publications

(24 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…But it is not always possible and, therefore, the implementation of more complex methods based in Computational Fluid Dynamics -CFD -are necessary. These simulations can be highly complex when, for example, an entire aircraft is modeled in order to study the effect of the fuselage in the vortex dynamic (Sustrino et al 2020) or even when an entire rocket is modeled with the grid using chimera technique (Oliveira Neto et al 2011). It is also possible to consider an intermediary situation in that CFD is applied in a more simplified and accessible way.…”

Section: Introductionmentioning

confidence: 99%

Development and Validation of an Open Source CFD Code for Analysis of Aerospace Vehicles

Souza,

Romano,

Passaro

et al. 2023

J. Aerosp. Technol. Manag.

View full text Add to dashboard Cite

In this work, a review of the theoretical aspects and an assessment to validate a Computational Fluid Dynamics (CFD) opensource code for applications in aerospace problems are discussed. The code uses a finite volume method, with cell-centered implementation, and it is suitable for simulations of inviscid, laminar, and turbulent flows. The code considers two-dimensional cases with unstructured meshes and employs the turbulence model known as Spalart-Allmaras. The implementation is detailed presenting the spatial discretization, including the upwind scheme, the linear reconstruction algorithm, and the calculation applying the method of gradients. The temporal discretization considers the application of a multistage explicit algorithm using a 5 stages Runge-Kutta method. The validation was done considering three cases of study: the inviscid shock tube, the laminar flat plate, and the flow over a rocket fairing. These cases are simulated using the software developed and the results are compared with analytical and experimental results. The rocket fairing case is related to the analysis of the Brazilian VLS launch during its transonic flight and it exemplifies the effect of the shock wave/boundary-layer interaction in its pressure distribution. The simulation results present a good agreement with the experimental results.

show abstract

Section: Introductionmentioning

confidence: 99%

Development and Validation of an Open Source CFD Code for Analysis of Aerospace Vehicles

Souza,

Romano,

Passaro

et al. 2023

J. Aerosp. Technol. Manag.

View full text Add to dashboard Cite

show abstract

Wind Tunnel Aerodynamic Study of a VTOL-UAV for Wide Range of Angles of Attack and Sideslip Angles

Prieto

Esteban

2020

Aerotec. Missili Spaz.

View full text Add to dashboard Cite

Vortex Dynamics Study and Flow Visualization on Aircraft Model with Different Canard Configurations

Wibowo

Basuki

Sutrisno

et al. 2021

Fluids

View full text Add to dashboard Cite

Canard configuration on fighter planes is essential for regulating flow and the occurrence of vortex interactions on the main wing, one of which is to delay stall. Stall delays are useful when the aircraft is making maneuvering or short-landing. This study observed the effect of canard configuration on various fighter aircraft models. Fighter models represented the different canard configurations, such as Sukhoi SU-30 MKI, Chengdu J-10, and Eurofighter Typhoon. Water tunnels and computational fluid dynamics (CFD) have made it easier to visualize the flow and aerodynamic forces. The results showed that at a low angle of attack (AoA) < 30°, the Chengdu J-10 and Eurofighter models had the highest lift force coefficient (Cl). When at high AoA, Cl’s highest value occurred on the Sukhoi SU-30 model with a value of 1.45 at AoA 50°. Meanwhile, the highest AoA that still had a high Cl value occurred on the Sukhoi SU-30 and Chengdu J-10 aircraft models, namely at AoA 55° with Cl values more than 1.1. The canard position in the upper of the wing would increase the Cl at low AoA, while the parallel canard position could delay the stall.

show abstract

Vortex Dynamics Analysis of Straight-Body-Type-Fuselage Fighter Using CFD Simulation

Cited by 3 publications

References 23 publications

Development and Validation of an Open Source CFD Code for Analysis of Aerospace Vehicles

Development and Validation of an Open Source CFD Code for Analysis of Aerospace Vehicles

Wind Tunnel Aerodynamic Study of a VTOL-UAV for Wide Range of Angles of Attack and Sideslip Angles

Vortex Dynamics Study and Flow Visualization on Aircraft Model with Different Canard Configurations

Contact Info

Product

Resources

About