• ABHISHEK KANAJE
• AASMI GUPTA
• ADITYA SHANKARNARAYANAN
• SMIT SHINDE
• TANVEE SHAH

This study presents a comprehensive computational fluid dynamics (CFD) investigation into the aerodynamic behavior of an open missile bay integrated into a delta wing platform under supersonic flow conditions. The primary objective is to analyze the internal flow structures, pressure distribution, and aerodynamic stability in configurations with and without internal missile stores. Using ANSYS Fluent, steady-state, density-based simulations were performed employing the SST (Shear Stress Transport) k-ε (k-epsilon) turbulence model to resolve complex shock interactions and recirculating flow features within the missile bay cavity. Two configurations were analyzed: one featuring a clean bay (without missiles) and another incorporating vertically aligned cylindrical missiles. The clean configuration exhibited a stable shear layer over the bay opening, a large coherent vortex structure within the cavity, and a symmetric pressure distribution — indicating minimal impact on structural loading and aircraft trim. In contrast, the inclusion of missiles significantly disrupted the internal flowfield, resulting in asymmetric vortex fragmentation, increased turbulence intensity, high-pressure stagnation zones, and complex wake interactions that elevated the drag and trim imbalance. Furthermore, various missile mounting positions on the delta wing were studied to determine their effect on aerodynamic performance and stability. The analysis showed that missiles mounted closer to the wing root introduced more substantial trim disturbances and central wake formation, while wingtip-mounted missiles exhibited more localized flow disruption and manageable aerodynamic penalties. The dual-missile configuration, though symmetrical, increased parasitic drag. Overall, the study provides valuable insights into missile bay aerodynamics and the strategic deployment of stores to optimize flight performance. These findings have critical implications for the design of stealth and high-speed aircraft, where minimizing acoustic signatures and preserving aerodynamic balance are paramount. Future work will focus on unsteady simulations, store separation modeling, and experimental validation to further refine deployment strategies and enhance design accuracy.

Delta wing, missile deployment, CFD, wake interaction, trim balance, pressure distribution, path line, missile store ejection

"Numerical flow investigation approach during off-trimming of missiles mounted under a fighter jet aircraft wing.", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.12, Issue 6, page no.j39-j53, June-2025, Available :http://www.jetir.org/papers/JETIR2506907.pdf

"Numerical flow investigation approach during off-trimming of missiles mounted under a fighter jet aircraft wing.", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.12, Issue 6, page no. ppj39-j53, June-2025, Available at : http://www.jetir.org/papers/JETIR2506907.pdf