A Drag and Flow Characteristics around the Hybrid Projectile

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Journal of the Korea Institute of Military Science and Technology 2000;3(2):23-34.

하이브리드탄의 항력 및 유동해석

이상길, 이동현

군사과학대학원 무기공학과

Abstract

Three dimensional, compressible, mass weighted averaging of Favre, Navier-Stokes system with k-$varepsilon$ turbulence, is numerically discretized to compute three dimensional multiple jet interaction flow fields for a hybrid projectile containing three rocket motors in the ogive section. Numerical flow field computations have been made for angled nose jets and rockets at supersonic speed using multiblock structured grid. The jet conditions include very high jet to free stream pressure ratio and high temperature. It is shown that the strength of nozzle stagnation pressure affects the flow field near the side nozzle and the high stagnation pressure increases total amount of drag by a few percent. However, minor drag loss due to the pressure drag might be fully overcomed by an additional axial thrust. The results of present study can be applied for the design of future hybrid projectile.

Key Words: Flux Difference Splitting, Upwind Schemes, Drag Coefficient, Hybrid Projectile, Scarfed Nozzle