Jet Effects on Cylindrical Afterbodies Housing Sonic and Supersonic Nozzles which Exhaust Against a Supersonic Stream at Angles of Attack from 90 to 180

Jet effects on cylindrical afterbodies housing sonic and supersonic nozzle

Experimental Investigation of Effects of Primary Jet Flow and Secondary Flow Through a Zero-length Ejector on Base and Boattail Pressures of a Body of Revolution at Free-stream Mach Numbers of 1.62, 1.93, and 2.41

An investigation was made at free-stream Mach numbers of 1.62, 1.93, and 2.41 to determine the effects of a primary jet and secondary air flow on the base pressure and pressures acting over the boattailsurface of a body of revolution for two secondary discharge areas. The Mach numbers of the primary nozzles were 1 and 3.23 with the secondary mass flow being varied from 0 to 10 percent of the primary mass flow. The ratio of jet stagnation temperature to tunnel stagnation temperature was about 0.96. The Reynolds number range of the investigation was from 2.1 x 10(6) to 2.9 x 10(6)based on body length. All testing was conducted with a turbulent boundary layer along the model. This report presents results obtained with zero-length ejector and covers jet static-pressure ratios from the jet-off condition to a maximum of about 128 for the sonic nozzle and to a maximum of about 9 for the supersonic nozzle

NACA Research Memorandums

Experimental values of damping in roll at zero angle of attack of the Douglas D-558-II research airplane and its components have been obtained at five different Mach numbers. Large effects of Reynolds number, boundary layer, and wing-incidence angle on the damping in roll were obtained

NACA Research Memorandums

Experimental values of damping in roll at zero angle of attack of the Bell X-1E research airplane and various combinations of components were obtained at 5 different Mach numbers. The damping in roll of the model was of the order predicted by theory. Results regarding the contributions of the airplane components and comparisons of experimental values with theoretical values are provided

NACA Research Memorandums

Memorandum presenting component interference studies that have been made in an attempt to explain the unexpected large loss in damping in roll which occurred in wind-tunnel tests at zero angle of attack for the Bell X-1A research airplane near a Mach number of 2.22. The studies include theoretical calculations of the effect of the body flow field on the wing damping in roll and measurements at several Mach numbers on the contribution of the individual components to the damping in roll