235 p.Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 1985.The mechanisms controlling the interactions between base flow induced irreversibilities with downstream effective critical flow conditions within rocket launch tubes due to friction and/or cross-sectional obstruction are studied here in detail. The analytical treatment by the flow component approach using one- and two-dimensional techniques is corroborated by a comprehensive experimental program.A full qualitative understanding of the very complex interactions of non-steady processes is attained by delineating the controlling mechanisms such as fluidic mass entrainment in the base region, mass storage, shock wave development and kinematics, and shock wave interactions wi...
The basic idea behind a solid rocket motor (SRM) is simple but its design is a complex technological...
Shock tube experiments are a key method of reproducing the flow conditions encountered by hypersonic...
The integration of the propulsion component plays a key role in the design process of future launche...
A numerical study on shocked flows induced by a supersonic projectile moving in tubes is described i...
In Part 1 a point-by-point method is developed for the calculation of unsteady flows through tubes w...
An analytical investigation is performed to study the unsteady response of a one-dimensional, non-li...
PREDICTION and control of pressure and pressure-rise rate during the ignition transient of solid-pro...
The aerodynamics around space launch vehicles determine the external forces that these vehicles expe...
A numerical study on wave dynamic processes occurring in muzzle blast flows, which are created by a ...
The turbulent wake flow of generic rocket configurations is investigated experimentally and numerica...
Rocket booster engines generally must operate at a large variety of atmospheric conditions. To achie...
Surveys of the fluctuating wall pressure were conducted on a sub-scale parabolic-contour rocket nozz...
Adetailed picture of the internal flow during the starting transient of high-performance solid rocke...
Shock tube experiments are a cornerstone of investigations into the hypersonic flight environment. H...
Shock tube experiments are a primary means of obtaining ground test data for the hypersonic regime. ...
The basic idea behind a solid rocket motor (SRM) is simple but its design is a complex technological...
Shock tube experiments are a key method of reproducing the flow conditions encountered by hypersonic...
The integration of the propulsion component plays a key role in the design process of future launche...
A numerical study on shocked flows induced by a supersonic projectile moving in tubes is described i...
In Part 1 a point-by-point method is developed for the calculation of unsteady flows through tubes w...
An analytical investigation is performed to study the unsteady response of a one-dimensional, non-li...
PREDICTION and control of pressure and pressure-rise rate during the ignition transient of solid-pro...
The aerodynamics around space launch vehicles determine the external forces that these vehicles expe...
A numerical study on wave dynamic processes occurring in muzzle blast flows, which are created by a ...
The turbulent wake flow of generic rocket configurations is investigated experimentally and numerica...
Rocket booster engines generally must operate at a large variety of atmospheric conditions. To achie...
Surveys of the fluctuating wall pressure were conducted on a sub-scale parabolic-contour rocket nozz...
Adetailed picture of the internal flow during the starting transient of high-performance solid rocke...
Shock tube experiments are a cornerstone of investigations into the hypersonic flight environment. H...
Shock tube experiments are a primary means of obtaining ground test data for the hypersonic regime. ...
The basic idea behind a solid rocket motor (SRM) is simple but its design is a complex technological...
Shock tube experiments are a key method of reproducing the flow conditions encountered by hypersonic...
The integration of the propulsion component plays a key role in the design process of future launche...