Investigation at Mach Number 1.91 of Spreading Characteristics of Jet Expanding from Choked Nozzles

It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are considerably smaller than the temperature profiles of jets expanding into quiescent air. The effect on the wake of varying afterbody geometry is shown to be small. The gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles in the base of a body of revolution with various boattail configurations at a Mach number of 1.91 are presented

Experimental Investigation of the Effects of Support Interference on the Pressure Distribution of a Body of Revolution at a Mach Number of 3.12 and Reynolds Numbers from 2 x 10(exp 6) to 14 x 10(exp 6)

A compilation of available information on the problem of support interference at transonic and supersonic speeds is presented. (author

NACA Research Memorandums

From Summary: "An experimental wind-tunnel investigation was conducted at Mach 1.9 to determine the pressures acting on the base of a multijet missile using unheated air and carbon dioxide as jet fluids. The variation of base pressure with jet static-pressure ratio was compared with results estimated for an axisymmetric single-jet model and some correlation was observed.

NACA Research Memorandums

It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are considerably smaller than the temperature profiles of jets expanding into quiescent air. The effect on the wake of varying afterbody geometry is shown to be small. The gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles in the base of a body of revolution with various boattail configurations at a Mach number of 1.91 are presented

NACA Research Memorandums

Report presenting data showing the effect of a jet on base pressure for a series of conical afterbody-jet-nozzle combinations with a range of boattail angles and base-to-jet diameter ratios. Generally, base pressure increased for increasing values of boattail angle, nozzle angle, jet temperature, and jet total pressure and for decreasing values of base-to-jet diameter ratio, jet Mach number, and free-stream Mach number

NACA Research Memorandums

Report presenting an experimental investigation performed to determine the effect on base and forebody pressures of using a sting modified with varying length splitter plates and fins instead of a conventional sting to support a cone-cylinder body of revolution