Location
Cocoa Beach, Florida
Start Date
3-4-1967 12:00 AM
Description
A generalized approach to the one-dimensional flow of a dissociated gas is presented. The flow is characterized by the flow parameters F, G, H, and I, and the degree of dissociation, which are defined. The equation of state and the equations for the dynamic and thermodynamic properties of the gas are presented for the dissociating gas. Equations are presented which give the aerothermodynamic flow properties as a function of the degree of dissociation, the frozen flow Mach number MF, and the initial values of G, H, and I for any arbitrary given flight condition. These equations are solved for the limiting subsonic and hypersonic solutions for the flow variables as the frozen flow Mach number MF tends towards zero and infinity, respectively. Several aspects of the physical significance of these results are discussed from the point of view of atmospheric planetary entry of an aerospace vehicle. The generalized nondimensional flow function F is defined in terms of the flow parameters G, H, and I , and is also given as a function of MF, H, and a, in general. This functional relationship is displayed in graphical form which is useful for determining various aspects of the resulting flow, and providing further insight into the flow process under consideration. Specifically, several flow regimes are delineated.
Generalized Dissociating Gas Flow
Cocoa Beach, Florida
A generalized approach to the one-dimensional flow of a dissociated gas is presented. The flow is characterized by the flow parameters F, G, H, and I, and the degree of dissociation, which are defined. The equation of state and the equations for the dynamic and thermodynamic properties of the gas are presented for the dissociating gas. Equations are presented which give the aerothermodynamic flow properties as a function of the degree of dissociation, the frozen flow Mach number MF, and the initial values of G, H, and I for any arbitrary given flight condition. These equations are solved for the limiting subsonic and hypersonic solutions for the flow variables as the frozen flow Mach number MF tends towards zero and infinity, respectively. Several aspects of the physical significance of these results are discussed from the point of view of atmospheric planetary entry of an aerospace vehicle. The generalized nondimensional flow function F is defined in terms of the flow parameters G, H, and I , and is also given as a function of MF, H, and a, in general. This functional relationship is displayed in graphical form which is useful for determining various aspects of the resulting flow, and providing further insight into the flow process under consideration. Specifically, several flow regimes are delineated.
