Part 23 급 수소연료전지 커뮤터기의 나셀의 스팬 방향 배치에 따른 공력 영향성 분석

Abstract

The implementation of multi-engine propulsion in next-generation hydrogen fuel cell aircraft introduces new challenges in aerodynamic integration, particularly concerning nacelle placement along the wing span. This study investigates the aerodynamic impact of varying nacelle spanwise positions through a comparative computational analysis. Five under-wing nacelle configurations were evaluated using Reynolds-Averaged Navier- Stokes (RANS) simulations, incorporating the Spalart-Allmaras turbulence model. Simulations were performed at a representative cruise condition with a freestream velocity of 110 m/s. Key aerodynamic parameters, lift coefficient, drag coefficient, and lift-to-drag ratio were assessed. The results reveal that nacelle positioning significantly influences aerodynamic performance, with overly inboard clustering degrading lift and wake structure, while moderately inboard or outboard placements offer improved flow symmetry and a lift-to-drag ratio ranging from 8.01 to 12.54, depending on nacelle placement. These findings provide valuable insights for early-stage design optimization in hydrogen aircraft propulsion systems, where aerodynamic efficiency must be balanced with structural and propulsion integration constraints.