Impact of Hypersonic Boundary Layer Transition on Skin Drag and Surface Heating on Blunt Cones

Knisely, Carleton P.; Haley, Christopher L.; Zhong, Xiaolin

doi:10.2514/6.2019-1134

Cited by 2 publications

References 16 publications

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Improved vortex lattice method for drag prediction of supersonic wings using shock cone modelling

Joshi,

Thomas,

Tan

et al. 2024

Preprint

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In the realm of supersonic design, obtaining data for numerous supersonic configurations amidst intricate flow conditions proves time-consuming due to the excessive costs associated with high-fidelity computational demands. Running iterative simulations over an extended period is often impractical or entails substantial expenses. This inherent challenge necessitates the adoption of low-order potential solvers with reasonable accuracy to generate datasets. In support of this objective, This study addresses the high computational costs of obtaining data for supersonic configurations by developing a low-order solver that combines the Taylor-Maccoll hypervelocity method (TMHM) with the supersonic vortex lattice method. This approach aims to provide accurate drag predictions in supersonic flows while minimizing computational demands. By integrating TMHM to calculate wave drag and skin friction drag and enhancing the vortex lattice method to handle shockwave impacts through panel matching, the solver achieves improved accuracy in lift and drag computations. Validation against experimental data shows a 20% reduction in drag prediction error compared to traditional vortex lattice methods, with a 2.01% error for low-shock angles. The method achieves accuracy rates between 90% and 95% across various configurations, including a 90% accuracy for delta wings, 85% for positive dihedral wings, and 95% for large sweptback angle designs, as confirmed by comparisons with high-fidelity CFD data.

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Improved vortex lattice method for drag prediction of supersonic wings using shock cone modelling

Joshi,

Thomas,

Tan

et al. 2024

Preprint

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Application of Broadband Receptivity Data to the Amplitude Method for Transition Prediction

Zhong

2023

Journal of Spacecraft and Rockets

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Conventional hypersonic transition prediction relies upon the highly empirical [Formula: see text] method, which is predicated on theoretical approximations of relative disturbance growth. This does not account for the receptivity mechanism and the high degree of variability present in experimental wind-tunnel conditions, which itself leads to high degrees of variability in transition [Formula: see text] factors. The amplitude method, which better approximates the broadband nature of boundary-layer disturbances, was previously proposed to account for the effects of receptivity. In this study, high-fidelity simulated second-mode receptivity data for two blunt cones at Mach 10 to broadband disturbances are applied to an iterative approximation of the amplitude method tuned for second-mode dominated flows. The studied geometries consist of 9.525- and 5.080-mm-nose-radius 7 deg half-angle straight cones based on experimental cases from Arnold Engineering Development Center’s wind tunnel 9. Amplitude method predictions show improvement over the accuracy of [Formula: see text] estimates using standard threshold [Formula: see text] factors. In particular, the less blunt 5.080 mm cone demonstrates the best agreement due to its stronger second-mode response. The results of this work provide a preliminary framework for applying high-fidelity receptivity simulations to the amplitude method for transition prediction in hypersonic flows.

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Impact of Hypersonic Boundary Layer Transition on Skin Drag and Surface Heating on Blunt Cones

Cited by 2 publications

References 16 publications

Improved vortex lattice method for drag prediction of supersonic wings using shock cone modelling

Improved vortex lattice method for drag prediction of supersonic wings using shock cone modelling

Application of Broadband Receptivity Data to the Amplitude Method for Transition Prediction

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