Space Marching Euler Solvers,
NAVAL SURFACE WEAPONS CENTER SILVER SPRING MD
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This paper focuses on space marching Euler solvers for tactical missiles. These solvers are applicable to missiles in supersonic flight provided that the flow field remains supersonic everywhere. The introductory section outlines progress to date and is followed by a discussion of numerical method which have been used to compute the flow about tactical missiles. Four different codes are described which are available for treating missile shapes. Results from these computational methods are presented for body-alone, body-wing-tail cases. Force coefficients, surface pressures and flow field predictions are compared to experiment. Reasonable agreement is obtained, illustrating the feasibility of using these methods in the design process. The limitation of the Euler equations are also discussed.
- Guided Missile Dynamics, Configurations and Control Surfaces
- Fluid Mechanics