Mathematical Modeling in Combustion Science

(0)

Erste Bewertung abgeben

An important new area of current research in combustion science is reviewed in the contributions to this volume. The complicated p...

20%

130.00

CHF104.00

Sie sparen CHF 26.00

Print on Demand - Exemplar wird für Sie besorgt.

Kartonierter Einband

Beschreibung

An important new area of current research in combustion science is reviewed in the contributions to this volume. The complicated phenomena of combustion, such as chemical reactions, heat and mass transfer, and gaseous flows, have so far been studied predominantly by experiment and by phenomenological approaches. But asymptotic analysis and other recent developments are rapidly changing this situation. The contributions in this volume are devoted to mathematical modeling in three areas: high Mach number combustion, complex chemistry and physics, and flame modeling in small scale turbulent flow combustion.
Inhalt
Shock-initiation of a plane detonation wave.- Effects of preignition fluctuation growth on reducing the induction period.- A lecture on detonation-shock dynamics.- Asymptotic analysis of branched-chain ignition in the counterflow field.- Asymptotic methods for flames with detailed chemistry.- Unsteady transition from sub- to supercritical evaporation regime.- High temperature extinction of premixed flames.- A model for lower deflagration limit and burning rate of catalyzed ammonium perchrolate.- An experimental study of tubular flames in rotating and non-rotating stretched flow fields.- Burning velocity of stretched flames.- Convection effects and the stability of hydrogen flame bubbles.- Characterization of turbulent premixed flame structure for mathematical modeling of combustion.- The stability of weakly stretched flames.- Extinction of counterflow diffusion flames with branching-termination chain mechanisms: Theory and experiment.- Some workshop topics.- Asymptotic approach to analysis of propellant combustion.- Onset of instability in a spherically growing flame.- Mg/TF propellant combustion.