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<p>Designing supersonic wings requires substantial resources, and the rapid generation of accurate data sets is crucial for the iterative design process. This research focuses on improving the current vortex lattice method (VLM) to enhance its capabilities for supersonic wing design. Four principal improvements are introduced: (i) advanced unsteady analysis modelling via the Unsteady VLM (UVLM) for better dynamic analysis, (ii) enhanced drag prediction through refined shockwave modelling using the Taylor-Maccoll hypervelocity approach (TMHM), which modifies the aerodynamic influence coefficient (AIC) matrix to account for shockcone interactions at each panel, (iii) improved compressibility correction by incorporating the multiphase lattice Boltzmann method (LBM) using a double distribution function on a D2Q9 lattice with a 6-moment equation for greater accuracy in supersonic flow, and (iv) integration of these improvements within the Tornado VLM framework. Verification and validation against Reynolds-averaged navier–stokes (RANS) and Unsteady RANS (URANS) simulations are performed for two supersonic configurations: the SCALOS canard aircraft and the Concorde delta wing. The improved VLM demonstrates reductions in drag coefficient prediction error of up to 21% compared to the standard VLM, while requiring significantly lower computational resources than RANS. These enhancements provide a cost-effective and efficient means of generating reliable aerodynamic data for supersonic wing design.</p>

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Improvements in vortex lattice method for design analysis of supersonic wings: verification and validation

  • 期刊论文

  • 发表日期：

    2026年6月29日

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  • Hemant Joshi,
  • Peter Thomas

摘要

Designing supersonic wings requires substantial resources, and the rapid generation of accurate data sets is crucial for the iterative design process. This research focuses on improving the current vortex lattice method (VLM) to enhance its capabilities for supersonic wing design. Four principal improvements are introduced: (i) advanced unsteady analysis modelling via the Unsteady VLM (UVLM) for better dynamic analysis, (ii) enhanced drag prediction through refined shockwave modelling using the Taylor-Maccoll hypervelocity approach (TMHM), which modifies the aerodynamic influence coefficient (AIC) matrix to account for shockcone interactions at each panel, (iii) improved compressibility correction by incorporating the multiphase lattice Boltzmann method (LBM) using a double distribution function on a D2Q9 lattice with a 6-moment equation for greater accuracy in supersonic flow, and (iv) integration of these improvements within the Tornado VLM framework. Verification and validation against Reynolds-averaged navier–stokes (RANS) and Unsteady RANS (URANS) simulations are performed for two supersonic configurations: the SCALOS canard aircraft and the Concorde delta wing. The improved VLM demonstrates reductions in drag coefficient prediction error of up to 21% compared to the standard VLM, while requiring significantly lower computational resources than RANS. These enhancements provide a cost-effective and efficient means of generating reliable aerodynamic data for supersonic wing design.