Space marching Euler solvers for tactical missiles are examined. 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 methods which were used to compute the flow about tactical missiles. Four different codes are described which are available for treating missile body shapes. Results from these computational methods are presented for body-alone, body-wing, and 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.
Space Marching Euler Solvers
1988
32 pages
Report
Keine Angabe
Englisch
NTIS | 1988
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AIAA | 1996
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Online Contents | 1996
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