Asymptotic calculation of the dynamics of self-sustained detonations in condensed phase explosives

2012 ◽  
Vol 710 ◽  
pp. 166-194 ◽  
Author(s):  
J. A. Saenz ◽  
B. D. Taylor ◽  
D. S. Stewart

AbstractWe use the weak-curvature, slow-time asymptotics of detonation shock dynamics (DSD) to calculate an intrinsic relation between the normal acceleration, the normal velocity and the curvature of a lead detonation shock for self-sustained detonation waves in condensed phase explosives. The formulation uses the compressible Euler equations for an explosive that is described by a general equation of state with multiple reaction progress variables. The results extend an earlier asymptotic theory for a polytropic equation of state and a single-step reaction rate model discussed by Kasimov (Theory of instability and nonlinear evolution of self-sustained detonation waves. PhD thesis, University of Illinois Urbana-Champaign, Urbana, Illinois) and by Kasimov & Stewart (Phys. Fluids, vol. 16, 2004, pp. 3566–3578). The asymptotic relation is used to study the dynamics of ignition events in solid explosive PBX-9501 and in porous PETN powders. In the case of porous or powdered explosives, two composition variables are used to represent the extent of exothermic chemical reaction and endothermic compaction. Predictions of the asymptotic formulation are compared against those of alternative DSD calculations and against shock-fitted direct numerical simulations of the reactive Euler equations.

2005 ◽  
Vol 98 (5) ◽  
pp. 053514 ◽  
Author(s):  
B. L. Wescott ◽  
D. Scott Stewart ◽  
W. C. Davis

2017 ◽  
Vol 122 (22) ◽  
pp. 225112 ◽  
Author(s):  
S. D. Wilkinson ◽  
M. Braithwaite ◽  
N. Nikiforakis ◽  
L. Michael

2019 ◽  
Vol 45 (3) ◽  
pp. 374-386 ◽  
Author(s):  
Kibaek Lee ◽  
Alberto M. Hernández ◽  
D. Scott Stewart

1994 ◽  
Author(s):  
F. Pommel

A procedure for blade design, using a time marching method to solve the Euler equations in the blade-to-blade plane is presented. This procedure uses an Office Nationale d’Etude et de Recherches Aeronautique flow solver. The classical slip conditions (no normal velocity component along the blade profile) has been replaced by another boundary conditions in such a way that the required pressure may be imposed directly. The orignal direct code was therefore transformed into an inverse solver. The unknows are calculated on the blade wall using the so-called compatibility relations. The blade geometry is then modified by resetting the wall parallel to the new flow field. The results obtained with this design process for a supersonic turbine blade of a space turbopump is presented.


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