Abstract

The objective of the study outlined in this paper was to develop the computationally e©cient algorithm for multidimensional numerical simulation of de§agration-to-detonation transition (DDT) in gas-fueled airbreathing pulse detonation engine (PDE). It is implied that the availability of such an algorithm will allow for more realistic estimates of PDE performances (speci¦c impulse, thrust, etc.) than those obtained with the presumption of direct detonation initiation. The new algorithm is based on the coupled Flame Tracking Particle (FTP) method implemented into the standard Computational Fluid Dynamics (CFD) code solving the Reynolds Averaged Navier Stokes equations by the control-volume technique. The coupled methodology has been applied to the two-dimensional (2D) numerical simulation of repeatable DDT in a propane-fueled PDE at Mach 3.0 §ight conditions at altitudes 9.3 and 16 km. The fuel-based speci¦c impulse was estimated as 1700 1800 s. The DDT was shown to be a feasible approach for practical PDEs.

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