The report presents an analysis predicting separation of a turbulent boundary layer over a cone-flare configuration with gas injected into the boundary layer ahead of separation point. Separation location and separation lengths are compared with experimental data obtained at Mach number of 6 and a range of Reynolds numbers. At the highest Reynolds numbers the extent of separation decreases with increasing Reynolds number. When compared to separation over cylinder-flare body it is found that the extent of separation is lower for the cone-flare configuration. (Author)."21 July 1971".Includes bibliographical references (page 13)The report presents an analysis predicting separation of a turbulent boundary layer over a cone-flare configuration w...
An experimental investigation has been made of turbulent boundary-layer separation associated with c...
Experiments to generate multiple shock waves in an axisymmetric model at hypersonic speeds were cond...
The object of the present work is to experimentally study the case of a turbulent boundary layer sub...
Experiments at supersonic speeds and at Mach 8 were conducted to determine the conditions which gove...
A turbulent boundary layer separated by a forward-facing step was observed on the cylindrical portio...
An investigation was conducted on a turbulent boundary layer near a smooth surface with pressure gra...
The present status of available information relative to the prediction of shock-induced boundary-lay...
The prediction of incipient separation due to shock wave interaction with a boundary layer is a crit...
The magnitude and the effects of boundary-layer separation on normal-force-curve slopes, centers of ...
A shock-related separation of a turbulent boundary layer has been studied and documented. The flow w...
This experimental study documents the development and separation of a hypersonic boundary layer prod...
The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semia...
An experimental investigation involving a thick, adiabatic, naturally turbulent, two-dimensional bou...
A turbulent boundary layer separated by a forward-facing step was observed on the cylindrical portio...
Boundary-layer transition location measurements were made on a 10-deg sharp cone in 23 wind tunnels ...
An experimental investigation has been made of turbulent boundary-layer separation associated with c...
Experiments to generate multiple shock waves in an axisymmetric model at hypersonic speeds were cond...
The object of the present work is to experimentally study the case of a turbulent boundary layer sub...
Experiments at supersonic speeds and at Mach 8 were conducted to determine the conditions which gove...
A turbulent boundary layer separated by a forward-facing step was observed on the cylindrical portio...
An investigation was conducted on a turbulent boundary layer near a smooth surface with pressure gra...
The present status of available information relative to the prediction of shock-induced boundary-lay...
The prediction of incipient separation due to shock wave interaction with a boundary layer is a crit...
The magnitude and the effects of boundary-layer separation on normal-force-curve slopes, centers of ...
A shock-related separation of a turbulent boundary layer has been studied and documented. The flow w...
This experimental study documents the development and separation of a hypersonic boundary layer prod...
The feasibility of determining Reynolds numbers of boundary layer transition on sharp, 10-deg, semia...
An experimental investigation involving a thick, adiabatic, naturally turbulent, two-dimensional bou...
A turbulent boundary layer separated by a forward-facing step was observed on the cylindrical portio...
Boundary-layer transition location measurements were made on a 10-deg sharp cone in 23 wind tunnels ...
An experimental investigation has been made of turbulent boundary-layer separation associated with c...
Experiments to generate multiple shock waves in an axisymmetric model at hypersonic speeds were cond...
The object of the present work is to experimentally study the case of a turbulent boundary layer sub...