Performance of multiple jet-exit installations
Internal aerodynamics and performance of clustered jet-exit installations at transonic speeds
JET EXHAUST↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Velocity, momentum, and stagnation heating measurements at the exit of a free jet jxB plasma accelerator.
Velocity, momentum and stagnation heating measurements at exit of free jxB plasma accelerator
VELOCITY MEASUREMENT↗
Experimental investigation of secondary jets from two-dimensional nozzles with various exit Mach numbers for hypersonic control application
Secondary jets from two-dimensional nozzles with various exit Mach numbers for hypersonic control application
TWO-DIMENSIONAL JET↗
Two-hundred sixty-in.-dia motor feasibility demonstration program. Volume VI - 260-SL MOTOR nozzle and exit cone assemblies. Book 1 - Text Final phase report
Design and material evaluation program for fabrication of large ablative motor nozzle and exit cone
ABLATING MATERIAL↗
Wind-tunnel investigation at Mach numbers from 3.0 to 6.8 of the static aerodynamic characteristics of modified Mercury exit and escape capsule configurations
Static aerodynamic characteristics of modified Mercury exit and escape capsule configurations at Mach numbers 3.0 to 6.8
STATIC STABILITY↗
Experimental performance evaluation of a 6.02- inch /15.29-cm/ radial-inflow turbine with an exit diffuser
Experimental performance evaluation of radial inflow turbine with exit diffuser
Futral, S. M., Jr.↗
Calculation of the recombination rate constants of diatomic gases according to the Mach number of the flow at the exit of a supersonic nozzle
Calculation of recombination rate constants of diatomic molecules according to Mach number of flow at supersonic nozzle exit
Nikolayev, G. N.↗
Dynamic stability of space vehicles. Volume 10 - Exit stability
Analytical methods for dynamic stability analyses of large launch vehicles during flight through and exit from earth atmosphere
Ringland, R. F.↗
Flow and wall-temperature sensitivity in parallel passages for large inlet to exit density ratios in subsonic flow
Analytical investigation of flow and wall temperature sensitivity in heated passages for large inlet to exit density ratios in subsonic flow of nuclear rocket
Reshotko, M.↗
Frequency response of a forced flow single tube boiler with inserts and exit restriction
Frequency response of forced flow single tube boiler with inserts and exit restriction
Goodykoontz, J. H.↗
Effect of jet velocity and axial location of nozzle exit on the performance of a twin-jet afterbody model at Mach numbers up to 2.2
Jet velocity and axial location of nozzle exit on performance of twin-jet afterbody model
Berrier, B. L.↗
Radial inflow turbine performance with an exit diffuser designed for linear static pressure variation
Radial inflow turbine performance with exit diffuser designed for linear static pressure variation
Kofskey, M. G.↗
Automatically deploying nozzle exit cone extension Patent
Automatically deploying nozzle exit cone extension
Ward, D. R.↗
Experimental evaluation of four transfer functions for a single tube boiler which are dynamically independent of exit restrictions
Experimental evaluation of four transfer functions for single tube boiler and demonstration of functions being independent of exit restrictions
Goodykoontz, J. H.↗
Radial in-flow turbine performance with exit diffusers designed for linear static pressure variation
Radial-inflow turbine performance with exit diffusers designed for linear static-pressure variation
Kofskey, M. G.↗
Dynamic flow angle measurements at the diffuser exit of a Mach 2.5 mixed compression inlet
An exploratory investigation was made to determine the magnitude of the dynamic flow angle at a single point in the diffuser exit of a Mach 2.50 inlet. Results indicate that the maximum flow angle variation was + or - 3 degrees except when vortex generators were installed in the subsonic diffuser. The amplitude of these flow angle fluctuations was directly related to the amplitude of the total pressure fluctuations at the probe survey point. Flow angle fluctuations as high as + or - 11 degrees were recorded when vortex generators were installed near the probe survey point.
Prati, W. M.↗
The effect of nozzle inlet shape, lip thickness, and exit shape and size on subsonic jet noise
Far field noise data were taken for convergent nozzles of various shapes and sizes at subsonic velocities exceeding 400 feet per second. For a circular nozzle, the nozzle inlet shape and lip thickness had no effect on the noise level, directivity, or spectra when compared at the same nozzle exit diameter and peak exhaust velocity. A sharp edged orifice was one exception to this statement. Coannular nozzles can produce additional high frequency noise. Blunt ended centerbodies, where there is significant base drag, also generate significant additional noise. The total noise power generation was essentially the same for circular, slot, and plug nozzles of good aerodynamic shape. The noise radiation patterns were essentially the same for these nozzle shapes except near the nozzle exhaust axis.
Olsen, W. A.↗
Special report, exit slit mirrors for the Ebert spectrometer
The use of a very long straight entrance slit in an Ebert grating spectrometer with two plane mirrors at the shorter exit slit to increase the energy density is described. This system has been employed in a far ultraviolet rocket spectrometer to provide higher sensitivity than has been achieved previously. The imaging properties and required slit and mirror adjustments are presented. Experimental results are included.
Fastie, W. G.↗