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Surrogate-assisted coupled CFD–compressor analysis for efficient aerodynamic evaluation of compressor-equipped Hyperloop vehicles.

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Bibliographic Details
Title: Surrogate-assisted coupled CFD–compressor analysis for efficient aerodynamic evaluation of compressor-equipped Hyperloop vehicles.
Authors: Kwon, Hyeokbin1 (AUTHOR) hbkwon@ut.ac.kr
Source: Journal of Mechanical Science & Technology. Aug2026, Vol. 40 Issue 8, p5959-5967. 9p.
Subjects: Compressor performance, Computational aerodynamics, Aerodynamics, Reduced-order models, Prediction models, Drag reduction, Motor vehicles
Abstract: An onboard compressor has been proposed to mitigate the Kantrowitz limit in Hyperloop systems, but directly resolving the internal compressor flow with conventional CFD is inefficient for iterative design. This study solves the external flow field using conventional CFD while evaluating compressor performance with a dedicated module. The two solvers are coupled iteratively by updating the compressor inlet mass flow rate until consistency is achieved. Using the converged coupled solutions, the compressor-induced drag reduction is quantified (up to 56.6 %). To reduce the cost of repeated coupling, a surrogate is introduced to replace the compressor module during iteration. A response surface model predicts compressor-inlet mass flow rate, total pressure, and total temperature from precomputed data over a design space defined by vehicle speed and inlet area. The surrogate achieves high accuracy (R2 = 0.999) and enables efficient aerodynamic analyses by prescribing inlet conditions directly at the compressor boundary. [ABSTRACT FROM AUTHOR]
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Database: Engineering Source
Description
Abstract:An onboard compressor has been proposed to mitigate the Kantrowitz limit in Hyperloop systems, but directly resolving the internal compressor flow with conventional CFD is inefficient for iterative design. This study solves the external flow field using conventional CFD while evaluating compressor performance with a dedicated module. The two solvers are coupled iteratively by updating the compressor inlet mass flow rate until consistency is achieved. Using the converged coupled solutions, the compressor-induced drag reduction is quantified (up to 56.6 %). To reduce the cost of repeated coupling, a surrogate is introduced to replace the compressor module during iteration. A response surface model predicts compressor-inlet mass flow rate, total pressure, and total temperature from precomputed data over a design space defined by vehicle speed and inlet area. The surrogate achieves high accuracy (R2 = 0.999) and enables efficient aerodynamic analyses by prescribing inlet conditions directly at the compressor boundary. [ABSTRACT FROM AUTHOR]
ISSN:1738494X
DOI:10.1007/s12206-026-0733-8