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• W1600660812 abstract "Recent developments in shock tunnel techniques have permitted experimentation in hypersonic airflows having very high enthalpies. In the present paper, the Cornell Aeronautical Laboratory 6 ft shock tunnel will be described, the effects of non-equilibrium flow in such a device will be assessed, and high-enthalpy experiments involving nozzle flow ionization will be discussed . The 6 ft shock tunnel at the Cornell Aeronautical Laboratory utilizes heated high-pressure hydrogen for a driver gas to obtain hypersonic airflows at high stagnation temperatures and pressures. Reflected shock operation is used with the tailored-interface technique to maximize the duration of steady flow. A significant portion of re-entry flight conditions can be duplicated for various hypersonic vehicles; however, partial simulation may be used to cover afar wider range of velocity and altitude. For measuring ionization levels and collision frequencies, microwave diagnostics have been recently employed . Owing to the high degrees of initial dissociation and the large expansion of the test gas, it has been necessary to study the influences of non-equilibrium chemistry and ionization on the conditions in the test section. To this end, a general numerical code has been developed for an IBM 704 computer in order to solve quasi-one-dimensional flows with coupled rate processes. Such theoretical studies are essential for planning and interpreting experiments in high-temperature tunnel flows. Solutions have been obtained for airflows with atoms, molecules, electrons, and ions reacting simultaneously. Investigations of various ion kinetic mechanisms have shown that processes such as charge transfer, impact ionization, and mutual neutralization may play significant roles under certain conditions of hypersonic flow in shock tunnels and about blunt bodies in flight . Preliminary experiments carried out in the shock tunnel have dealt with non-equilibrium ionization. Phase shift of microwaves passed through the airflow in the tunnel nozzle has yielded information on deionization kinetics and on the duration of useful test flow. Critical frequencies far below the microwave band are indicated for the gas over the entire range of conditions in the test section. These experiments have indicated that flows of high enthalpy can be generated by shock tunnels for the detailed study of the ionized shock layer on a hypersonic vehicle." @default.
• W1600660812 created "2016-06-24" @default.
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• W1600660812 date "1964-01-01" @default.
• W1600660812 modified "2023-09-26" @default.
• W1600660812 title "Shock Tunnel Studies of High-Enthalpy Ionized Airflows* *This work was supported by the Office of Scientific Research, Mechanics Division, under Contract AF 49(638)-952; by the Office of Naval Research, Mathematical Sciences Division under Contract Nonr 2653(00); and by CAL Internal Research." @default.
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• W1600660812 doi "https://doi.org/10.1016/b978-1-4831-9828-6.50016-3" @default.
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