Numerical simulation of separated supersonic flows around tactical missile bodies
Numerical simulation of separated supersonic flows around tactical missile bodies
- New search for: Guillen, P.
- New search for: Lordon, J.
- New search for: Guillen, P.
- New search for: Lordon, J.
Beyond four or five degrees of incidence, vortices develop on the leeside of tactical missile fuselages. This paper presents the validation of a numerical approach to simulate these separated flows. In this approach the flow is computed by solving the Euler equations and separation is forced by a local treatment (Kutta condition like) on the body of the missile, near the supposed location of the separation line, which has to be known. This local treatment has been implemented in two different Euler solvers. Results are presented for various configurations and different aerodynamic conditions. The influence of several parameters has been investigated. Finally some calculations show the interest of the method to evaluate the vortical flow interaction with wings.
Document information
Numerical simulation of separated supersonic flows around tactical missile bodies
Numerische Simulation getrennter Ueberschallstroemungen um taktische Raketenkoerper
Validation of Computational Fluid Dynamics ; 1 , Dec ; P-18
1988
18 Seiten, 23 Bilder, 15 Quellen
Conference paper
English
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