CFD Analysis of Weapon Bay Missile Ejection at Various Mach Numbers

The aerodynamic behaviour of missiles released from weapon bay cavities at supersonic velocities ranging from Mach 2 to Mach 5 is studied. The computation offers detailed examinations of the pressure fluctuations, the density variations, and the Mach number distributions. A particular attention is focused on the interaction of the shear layer at the leading edge of the cavity with the shock generated on the missile nose. The findings indicate minimal changes in the interaction between the shear layer at the cavity’s leading edge and the leading-edge shock produced at the missile’s nose at the Mach number range from 2 to 5. At the Mach number equal to 2, the interaction is relatively subdued, mainly affected by a detached shock wave with increased flow turning angle. Prandtl–Meyer expansion on both the nose tip and the tail end of the missile highlights the influence of compressibility. In contrast, at the Mach numbers equal to 3, 4, and 5, the interaction between the shear layer and the shock wave system becomes a notable factor that affects aerodynamic changes. In contrast, an intense detached bow shock wave prevails at the Mach number equal to 2. These findings offer crucial insights into the intricate flow dynamics surrounding missiles at high supersonic velocities, with implications for enhancing aerodynamic design and optimizing performance in future aerospace endeavours.