A Multi-fidelity Aerodynamic Modelling Approach for NATO AVT 251 UCAV – MULDICON

Kaya, Halil; Tiftikci, Hakan; Kutluay, Umit; Sakarya, Evren

doi:10.2514/6.2018-3000

Cited by 3 publications

(1 citation statement)

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“…Most of the researchers previously had worked to understand and mitigate the unsteadiness and uncertainties of the flow to make the C m predictable and consistent at a medium to a higher AOA for the low sweep lambda wing by conducting only the computational fluid dynamics (CFD) simulation work. However, different CFD techniques failed to predict consistent results for the nonlinear region at a medium to a higher AOA, as highly complex and nonlinear flow topology existed, which always resulted in the over-prediction and under-prediction of the CFD results at medium to higher AOA (Kaya et al , 2018; Nangia et al , 2019; van Rooij et al , 2018). There is a definite need to use several experimental flow visualization and the aerodynamic loads measurements methods to understand the flow topology and pitching moment coefficient at medium to a higher AOA.…”

Section: Introductionmentioning

confidence: 99%

Flow characterization of low sweep MULDICON wing at low speed

Haider

Mansor

Mat

et al. 2023

AEAT

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Purpose The flow topology for multi-disciplinary configuration (MULDICON) wing is very complicated and nonlinear at low to high angle of attack (AOA). This paper aims to provide the correlation between the unsteadiness and uncertainties of the flow topology and aerodynamic forces and moments above MULDICON WING at a medium to a higher AOA. Design/methodology/approach The experimental and computational fluid dynamics methods were used to investigate a generic MULDICON wing. During the experiment, the AOA were varied from α = 5° to 30°, whereas yaw angle varies between β = ±20° and Reynolds number between Re = 3.0 × 105 and Re = 4.50 × 105. During the experiments steady-state loading, dynamic loading and flow visualization wind tunnel methods were used. Findings The standard deviation quantified the unsteadiness and uncertainties of flow topology and predicted that they significantly affect the pitching moment (Cm) at medium to higher AOA. A strong correlation between flow topology and Cm was exhibited, and the experiment data was well validated by previous numerical work. The aerodynamic center was not fixed and shifted toward the wing apex when AOA is increasing. For a = 10°, the flow becomes more asymmetric. Power spectral densities plots quantify the flow separation (apex vortex, leading-edge vortex and vortex breakdown) over the MULDICON wing. Originality/value The application and comparison of steady-state and dynamic loading data to quantify the unsteadiness and uncertainties of flow topology above the MULDICON wing.

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Section: Introductionmentioning

confidence: 99%