Multi-disciplinary simulations of stores in weapon bays using scale adaptive simulation

Loupy, Gaëtan J.; Barakos, George N.; Taylor, Nigel J.

doi:10.1016/j.jfluidstructs.2018.05.012

Cited by 9 publications

(4 citation statements)

References 28 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For the SAS formulation, an additional source term is added to the k − ω Shear Stress Transport (SST) equations which allows for the local adjustment of the von-Karman length scale and balances the contributions from resolved and statistical components. The SAS formulation in HMB3 has been used in the past for transonic cavity flows [31], missile projection [32] and stall flutter predictions [33]. This investigation was conducted to ensure that the standard URANS formulation closed with the k − ω turbulence model is accurate enough to capture the correct physics.…”

Section: Comparison Of Standard Urans and Scale-resolving Methodsmentioning

confidence: 99%

Numerical Investigation of a Two-Bladed Propeller Inflow at Yaw

Higgins

Zarev

Barakos

et al. 2020

Journal of Aircraft

View full text Add to dashboard Cite

Section: Comparison Of Standard Urans and Scale-resolving Methodsmentioning

confidence: 99%

Numerical Investigation of a Two-Bladed Propeller Inflow at Yaw

Higgins

Zarev

Barakos

et al. 2020

Journal of Aircraft

View full text Add to dashboard Cite

“…The SAS formulation adds an additional source term to the k − ω SST equations, which allows the local adjustment of the von Karman length scale and balances contributions from the resolved and statistical components. The SAS implementation in HMB3 has been used for studies of cavity flows [17], missile projection [18], and stall flutter [19].…”

Section: B Hmb3 Solvermentioning

confidence: 99%

Development of Simulation Tools for High Fidelity Analysis of Compound Rotorcraft

Zhang

Barakos

2020

AIAA Scitech 2020 Forum

View full text Add to dashboard Cite

This paper presents the development and validation of a tool chain for high-fidelity analysis of compound rotorcraft. An automatic geometry composition and grid generation framework is constructed using ICEM Hexa scripts and in-house codes. Simulation methods of various fidelity levels are then put forward and evaluated. The framework is examined and validated through simulations of ducted propeller cases. The high fidelity CFD simulations are performed using the HMB3 solver. Comparisons and validation are made with experimental data, as well as simpler predictive methods. The ducted propeller shows superior performance over its un-ducted counterpart at low or moderate advance ratios. The ducted propeller also shows less intrusive wake features. The major thrust gain is identified to originate from the duct itself. As the advance ratio increases, the duct thrust contribution becomes negative and the ducted propeller thus becomes deficient. Cross-wind conditions are also considered. The duct is found to be the source of the large lift force and the nose-up pitching moment. Detailed analyses of the duct surface pressure and the propeller induction are presented.

show abstract

“…HMB3 SAS simulations have been conducted in the past focusing on transonic cavity flows [30] and missile projection [31]. Because this investigation requires the deformation and relative motion of the propeller blade, in order to achieve this, the chimera method is used [32].…”

Section: Computational Fluid Dynamicsmentioning

confidence: 99%

High-Fidelity Computational Fluid Dynamics Methods for the Simulation of Propeller Stall Flutter

et al. 2019

View full text Add to dashboard Cite

Brown, N. (2019) Highfidelity computational fluid dynamics methods for the simulation of propeller stall flutter. A time-marching aeroelastic method developed for the study of propeller flutter is presented and validated. Propeller flutter can take many forms with stall, whirl and classical flutter being the primary responses. These types of flutter require accurate capture of the non-linear aerodynamics associated with propeller blades. Stall flutter in particular needs detailed unsteady flow modelling. With the development of modern propeller designs potentially adjusting the flutter boundary and the development of faster computing power, CFD is required to ensure accurate capture of aerodynamics. Given the lack of reliable experimental stall flutter data for propellers, the method was focused on observing the correct qualitative behaviour with a comparison made between URANS and Scale-Adaptive Simulation (SAS). Greek α s m = Model amplitude of mode m of solid s (m/kg) ζ m = Damping coefficient (-) ρ = Fluid density (kg/m 3 ) ψ s m = Normalised m th mode displacement of solid s (m/kg) ψ s = Normalised displacement of solid s (m/kg) ω m = Natural frequency of mode m Ω CV = Control volume size Subscripts i, j, k = Mesh cell indices

show abstract

Multi-disciplinary simulations of stores in weapon bays using scale adaptive simulation

Cited by 9 publications

References 28 publications

Numerical Investigation of a Two-Bladed Propeller Inflow at Yaw

Numerical Investigation of a Two-Bladed Propeller Inflow at Yaw

Development of Simulation Tools for High Fidelity Analysis of Compound Rotorcraft

High-Fidelity Computational Fluid Dynamics Methods for the Simulation of Propeller Stall Flutter

Contact Info

Product

Resources

About