Author: Leroy L. PresleyPublisher:
ISBN:
Category : Chemical reactions
Languages : en
Pages : 10
Book Description
Exact Solutions of Reflected Normal Shock-wave Flow Fields with Nonequilibrium Chemical Reactions
Author: Leroy L. PresleyPublisher:
ISBN:
Category : Chemical reactions
Languages : en
Pages : 10
Book Description
Numerical Solutions of Several Reflected Shock-wave Flow Fields with Nonequilibrium Chemical Reactions
Author: Ronald K. HansonPublisher:
ISBN:
Category : Chemical reactions
Languages : en
Pages : 60
Book Description
The method of characteristics for a chemically reacting gas is used in the construction of the time-dependent, one-dimensional flow field resulting from the normal reflection of an incident shock wave at the end wall of a shock tube. Nonequilibrium chemical reactions are allowed behind both the incident and reflected shock waves. All the solutions are evaluated for oxygen, but the results are generally representative of any inviscid, nonconducting, and nonradiating diatomic gas. The solutions clearly show that: (1) both the incident- and reflected-shock chemical relaxation times are important in governing the time to attain steady state thermodynamic properties; and (2) adjacent to the end wall, an excess-entropy layer develops wherein the steady state values of all the thermodynamic variables except pressure differ significantly from their corresponding Rankine-Hugoniot equilibrium values.
Inviscid, Nonequilibrium Flow Behind Bow and Normal Shock Waves: General analysis and numerical examples, by P. V. Marrone
Author: Cornell Aeronautical LaboratoryPublisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 120
Book Description
Chemical Non-equilibrium Shock Flow
Author: V. A. LangeloPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 70
Book Description
The problem of calculating the flow behind a normal shock front is discussed. The additional complication of finite reaction rate chemistry has been included. A numerical method and several results of flow across a shock wave with an eleven-species, thirteen reaction model of air are presented. Results of the method are discussed and compared with those of Hall, Escheroeder, and Marrone (inviscid hypersonic air flows with coupled non-equilibrium processes. IAS 30th annual meeting, Jan 1962). (Author).
Non-equilibrium Flow Fields with Chemical Reactions in a Shock Tube
Author: Elihu ZimetPublisher:
ISBN:
Category :
Languages : en
Pages : 78
Book Description
The two chemical reactions given by N2O4 + M = 2NO2 + M = 2NO + O2 + M, where M represents the inert carrier gases argon or nitrogen, were studied. The experiments were carried out in a temperature controlled shock tube and a light absorption technique permitted the time dependent concentration of the species NO2 to be determined. For shock strengths where the temperature did not exceed 400K only the first chemical reaction took place. Stronger shock waves excited both chemical reactions with temperatures up to 2100K, and for this reason, flow fields with two nonequilibrium modes could be investigated. Since the relaxation times of these two reactions were different by about three orders of magnitude, they could be experimentally uncoupled. A study of the reaction mechanisms and rate constants for both reactions was carried out. At shock strengths exciting only the first chemical reaction the complete picture of a non-equilibrium flow field with only one nonequilibrium mode could be investigated. In this situation, the shock strengths were varied from weak, fully dispersed waves to strong, partly dispersed waves. (Author).
Nonequilibrium Flow Fields Behind Reflected Shock Waves
Author: Harold Joseph BrandonPublisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 296
Book Description
A Graphical Solution of Shock Equations
Author: Charles E. TreanorPublisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 88
Book Description
Numerical Results for the Diffraction of a Normal Shock Wave by a Sphere and for the Subsequent Transient Flow
Author: Richard W. BarnwellPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 44
Book Description
The finite-difference method which Peter D. Lax developed for treating unsteady inviscid flow fields is used to study the transient flow in the shock layer of a sphere that has been struck by a normal shock wave. Transient flow of this sort is encountered when a shock tube is used as a supersonic wind tunnel. Time histories of the shock detachment distance and the stagnation-point pressure and tangential velocity gradient are presented for ranges of the incident-shock Mach number and the perfect-gas specific-heat ratio. These results show that the stagnation-point pressure approaches the steady value much more rapidly than the shock detachment distance. In general, the stagnation-point pressure but more rapidly than the shock detachment distance. As the specific-heat ratio is decreased and the incident-shock Mach number is increased, the variation of the velocity gradient with respect to the shock detachment distance becomes more nearly linear.
Author: Brown University
Author: