Abstract
Atmospheric and space launch stage separation depends on the aerodynamic interference between separating bodies. Quick means of estimating and controlling repulsion or attraction lift associated with this interaction are an important enabling technology to achieve the best compromise between launch separation rocket motor weight and safe staging. Asymptotic methods, scattering, and slender-body theories are used to obtain systematic approximation schemes that advantageously couple with computational methods. Theoretical solutions for the lift interference between two bodies in supersonic flow agree well with numerical solutions. The theory sheds light on important scattering phenomena not previously recognized as relevant to this problem. The analysis helps to identify lumped dimensionless parameters and provides scaling laws as well as closed-form expressions for the interference not accessible solely from computations. These results can be used for interpolation and extrapolation of computational fluid dynamics solutions as well as efficient testing and design of flight vehicles.
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