Add to ORKGIt 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
An experimental program was conducted to investigate the interaction effects which occur between the...
The objective of this investigation was to evaluate the effects of individual jet exhaust properties...
The results show that the jet spreads more rapidly as its density becomes lower than that of the rec...
It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are cons...
The Mach number and temperature profiles in jets expanding from convergent and convergent-divergent ...
The Mach number and temperature profiles in jets expanding from convergent and convergent-divergent ...
A series of rocket motors with varying exit to throat area ratios was tested in the 8- by 6-foot win...
The interaction of the flow from one convergent and two convergent-divergent nozzles on parabolic af...
An experimental investigation was conducted to determine the temperature profiles downstream of heat...
An investigation was conducted in the 8-by-6 foot supersonic wind tunnel on the effect of exhaust-ga...
Three 7.5 degree boattail bodies of revolution with varying base-annulus areas and jet sizes provide...
Results of an experimental and analytical research investigation on nozzle/afterbody drag are presen...
Experimental investigations were carried out on a typical axisymmetric configuration having a circul...
Experimental investigations were carried out in 0.3m trisonic wind tunnel at NAL to study the effect...
Preliminary results are presented from an investigation to determine the influence of afterbody geom...
An experimental program was conducted to investigate the interaction effects which occur between the...
The objective of this investigation was to evaluate the effects of individual jet exhaust properties...
The results show that the jet spreads more rapidly as its density becomes lower than that of the rec...
It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are cons...
The Mach number and temperature profiles in jets expanding from convergent and convergent-divergent ...
The Mach number and temperature profiles in jets expanding from convergent and convergent-divergent ...
A series of rocket motors with varying exit to throat area ratios was tested in the 8- by 6-foot win...
The interaction of the flow from one convergent and two convergent-divergent nozzles on parabolic af...
An experimental investigation was conducted to determine the temperature profiles downstream of heat...
An investigation was conducted in the 8-by-6 foot supersonic wind tunnel on the effect of exhaust-ga...
Three 7.5 degree boattail bodies of revolution with varying base-annulus areas and jet sizes provide...
Results of an experimental and analytical research investigation on nozzle/afterbody drag are presen...
Experimental investigations were carried out on a typical axisymmetric configuration having a circul...
Experimental investigations were carried out in 0.3m trisonic wind tunnel at NAL to study the effect...
Preliminary results are presented from an investigation to determine the influence of afterbody geom...
An experimental program was conducted to investigate the interaction effects which occur between the...
The objective of this investigation was to evaluate the effects of individual jet exhaust properties...
The results show that the jet spreads more rapidly as its density becomes lower than that of the rec...