Designing a vehicle for Mach 2.5 flight presents unique challenges, particularly in the transonic regime. For the Plasma Dart, we utilized advanced CFD (Computational Fluid Dynamics) to optimize the nose cone fineness ratio and fin planform.
Shock Wave Management
At supersonic speeds, shock waves become the dominant factor in drag. Our simulations focused on minimizing the wave drag by employing a Haack series nose cone geometry. The results showed a significant reduction in pressure drag compared to traditional ogive shapes.
Thermal Considerations
Aero-heating at Mach 2.5 is significant. We've selected a high-temperature epoxy for the carbon fiber airframe and a titanium tip for the nose cone to handle the stagnation point temperatures.