By A. P. Bruckner (auth.), Professor K. Takayama, Associate Professor A. Sasoh (eds.)
Ram accelerators are one of the such a lot complex instruments for producing fluid dynamcis facts in supersonic reacting platforms. They require the mixed motion of combustion, wave structures and turbulence and are nonetheless a significant problem for physicists and engineers. This e-book will function an introductionary textbook on ram accelerators and provides an intensive evaluate on examine actions, functionality modeling and high-pressure detonation dynamics.
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Additional info for Ram Accelerators: Proceedings of the Third International Workshop on Ram Accelerators Held in Sendai, Japan, 16–18 July 1997
Sample text
2. 1 Calculation of equilibrium composition The calculation proceeds through a series of steps which, at all times involve many iterations. The equilibrium composition of the combustion products is calculated for each of these iterations and, therefore, it is one of the key operations of the calculation procedure. The calculation is based on the minimization of Gibbs free energy, but the iterative technique may differ from one case to another. A new technique based on matrix algebra was developed (Heuze et al.
1998). As the projectile accelerates, the normal shock recedes and eventually falls off the body. The flowfield described here presents three limits on the Mach number range of ram accelerator operation; a minimum Mach corresponding to that at which the incoming flow will just reach sonic velocity at the throat, a minimum Mach which is greater than the geometric constraint, yet is just at the point where the combustion heat release drives the normal shock up to the throat, and a maximum Mach which corresponds to the point where the shock falls off the Ram accelerator performance modeling 29 projectile body, or recedes completely behind the projectile in the case when it has a pointed tail (Hertzberg et al.
Gatau et al. (1995) have applied a quasi-steady, quasione-dimensional flowfield model to the axisymmetric projectile experiments with good results; however, they did not address the issue of drag. A similar propulsive cycle analysis was carried out with the inclusion of drag effects by Knowlen et al. (1996) . This theoretical model can readily be applied to examine the effects of geometry variations and propellant chemistries on the thrustMach number performance of a superdetonative ram accelerator.