The design of exhaust mufflers using linearized theoretical models
Optimal design for noise attenuation by diesel engine exhaust mufflers using linearized acoustic models
Alfredson, R. J.↗
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Flow characteristics in the exhaust of a pulsed magawatt gas fed arc
Transient pressure measurement in plasma exhaust flow of 500 microsec duration, discussing discharge temporal behavior and cold gas pressure front existence
Michels, C. J.↗
Temporal survey of electron number density and electron temperature in the exhaust of a megawatt MPD-Arc thruster
Temporal and radial profiles are obtained 30 cm downstream from the anode for two peak arc currents (11.2 kA and 20 kA) and for various auxiliary magnetic fields (0, 1.0 T, and 2.0T) using the Thomson scattering technique. Average density and temperature are relatively constant for over 100 microseconds with significant fluctuations. Radial profiles obtained are relatively flat for 4 cm from the axis. Compared to earlier 20 cm data, the exhaust density has decreased significantly, the average temperature (4.6 eV) has not changed, and the density hole with an auxiliary magnetic field has enlarged.
Michels, C. J.↗
Effect of operating conditions on the exhaust emissions from a gas turbine combustor
Exhaust concentrations of total unburned hydrocarbons, carbon monoxide, and nitric oxide were measured from a single J-57 combustor liner installed in a 30 diameter test section. Tests were conducted over a range of inlet total pressures from 1 to 20 atmospheres, inlet total temperatures from 310 to 590 K, reference velocities from 8 to m/sec, and fuel-air ratios from 0.004 to 0.015. Most of the data were obtained using ASTM A-1 fuel; however, a limited number of tests was performed with natural gas fuel. Combustion efficiency and emission levels are correlated with operating conditions. Sampling error at operating conditions for which combustion efficiency was below about 90 percent resulted in abnormally low readings for hydrocarbon emissions.
Briehl, D.↗
Rocket exhaust plume computer program improvement. Volume 1: Summary: Method of characteristics nozzle and plume programs
A summary is presented of the various documents that discuss and describe the computer programs and analysis techniques which are available for rocket nozzle and exhaust plume calculations. The basic method of characteristics program is discussed, along with such auxiliary programs as the plume impingement program, the plot program and the thermochemical properties program.
Ratliff, A. W.↗
Correlation of total sound power and peak sideline OASPL from jet exhausts
An empirical analysis of jet noise is made for convergent exhaust nozzles. An engineering approach to the correlation of total sound power and miximum sideline overall sound pressure level (OASPL), at 200 ft, is presented for both subsonic and supersonic jets based on available data. Data correlation for subsonic jets shows no dependency of total sound power and maximum sideline OASPL on jet density. The analysis for supersonic jets results in a correlation parameter for jet total sound power consisting of the conventional Lighthill parameter modified by considerations of jet Mach number and jet acoustic velocity. Similar parameters also correlate the maximum sideline OASPL for supersonic jets.
Vonglahn, U. H.↗
Exhaust flow and propulsion characteristics of a pulsed MPD arc thruster
An experimental investigation of the near-field megawatt, single-shot exhaust is presented for the self-field and auxiliary field cases (0-2 T). Plasma impact pressure and number density are correlated to provide velocity profiles (30,000 to 70,000 m/sec), thrust (10 to 120 N), impulse (3 to 16 N-sec) and mass accounting. The data agree with Hugel's self-field theory for the case where thrust is produced entirely by electromagnetic force. The data show that the thrust monotonically increases with auxiliary field.
Michels, C. J.↗
Temporal survey of electron number density and electron temperature in the exhaust of a megawatt MPD-arc thruster.
Temporal and radial profiles are obtained 30 cm downstream from the anode for two peak arc currents (11.2 kA and 20 kA) and for various auxiliary magnetic fields (0, 1.0 T, and 2.0 T) using the Thomson scattering technique. Average density and temperature are relatively constant for over 100 microseconds with significant fluctuations. Radial profiles obtained are relatively flat for 4 cm from the axis. Compared to earlier 20 cm data, the exhaust density has decreased significantly, the average temperature has not changed, and the density ?hole' with an auxiliary magnetic field has enlarged.
Michels, C. J.↗
Exhaust plume structure in a quasi-steady MPD arc.
Results of spectroscopic and photographic investigations revealing a complex azimuthal species structure in the exhaust plume of a quasi-steady argon MPD arc. The features of the plume structure are found to be dependent on the arc current and mass flow rate. Time-resolved spectroscopic velocity measurements, obtained by a scanning Fabry-Perot interferometer, indicate argon ion jet velocities of 16,500 m/sec at a current of 16 kA and a matched mass flow of 6 g/sec. It is found that nearly half this velocity is attained in an acceleration region well downstream of the region of significant electromagnetic interaction. Temperature measurements suggest that simple expansion processes in the argon jets cannot fully explain the observed acceleration. It is possible that a transfer of momentum from the ablated core flow to the argon jets may contribute to the high argon velocities.
Bruckner, A. P.↗
Exhaust flow and propulsion characteristics of a pulsed MPD arc thruster.
Experimental investigation of the near-field, megawatt, single-shot exhaust for the self-field and auxiliary field cases (0 to 2 tesla) for a pulsed MPD arc thrustor. Plasma impact pressure and number density are correlated to provide velocity profiles (30,000 to 70,000 m/sec), thrust (10 to 120 N), impulse (3 to 16 N-sec) and mass accounting. The data agree with Hugel's self-field theory for the case where thrust is produced entirely by electromagnetic force. The data show that the thrust monotonically increases with auxiliary field.
Michels, C. J.↗
Three dimensional nozzle-exhaust flow field analysis by a reference plane technique.
A numerical method based on reference plane characteristics has been developed for the calculation of highly complex supersonic nozzle-exhaust flow fields. The difference equations have been developed for three coordinate systems. Local reference plane orientations are employed using the three coordinate systems concurrently thus catering to a wide class of flow geometries. Discontinuities such as the underexpansion shock and contact surfaces are computed explicitly for nonuniform vehicle external flows. The nozzles considered may have irregular cross-sections with swept throats and may be stacked in modules using the vehicle undersurface for additional expansion. Results are presented for several nozzle configurations.
Dash, S. M.↗
Correlation of total sound power and peak sideline OASPL from jet exhausts.
An empirical analysis of jet noise is made for convergent exhaust nozzles. This study, conducted at the Lewis Research Center, presents an engineering approach to the correlation of total sound power and maximum sideline OASPL (at 200 ft) for both subsonic and supersonic jets based on available data. Data correlation for subsonic jets shows no dependency of total sound power and maximum sideline OASPL on jet density. The analysis for supersonic jets results in a correlation parameter for jet total sound power consisting of the conventional Lighthill parameter modified by considerations of jet Mach number and jet acoustic velocity. Similar parameters also correlate the maximum sideline OASPL for supersonic jets.
Von Glahn, U. H.↗
Flyover and static tests to investigate external flow effect on jet noise from nonsuppressor and suppressor exhaust nozzles
The effect of external air flowing across exhaust nozzles on the jet noise characteristics of supersonic transport aircraft at high takeoff speeds was investigated. A series of flyover and static tests were conducted using an F-106B aircraft modified with two underwing nacelles each containing a calibrated J85-GE-13 turbojet engine. Comparison of flyover and static data indicated that external flow reduces the noise of an auxiliary inlet ejector nozzle. An unsuppressed plug nozzle was not affected while the plug suppressor configurations were not as effective in flight.
Burley, R. R.↗
Effects of prevaporized fuel on exhaust emissions of an experimental gas turbine combustor
Effects of fuel vaporization on the exhaust emission levels of oxides of nitrogen (NOX), carbon monoxide, total hydrocarbons, and smoke number were obtained in an experimental turbojet combustor segment. Two fuel injector types were used in which liquid ASTM A-1 jet fuel and vapor propane fuel were independently controlled to simulate varying degrees of vaporization. Tests were conducted over a range of inlet-air temperatures from 478 to 700 K (860 to 1260 R), pressures from 4 to 20 atmospheres, and combustor reference velocities from 15.3 to 27.4 m/sec (50 to 90 ft/sec). Converting from liquid to complete vapor fuel resulted in NOX reductions as much as 22 percent and smoke number reductions up to 51 percent.
Norgren, C. T.↗
Effect of pressure on tangential-injection film cooling in a combustor exhaust stream
A tangential-injection film cooled test section was placed in the exhaust stream of a high pressure combustor. Film cooling data were taken at pressure of 1, 10, and 20 atmospheres. The film cooling effectiveness was found to be independent of pressure. The data were correlated adequately by a turbulent-mixing film cooling correlation with a turbulent-mixing coefficient of 0.05 + or - 0.02.
Marek, C. J.↗
The Formation of Hydrochloric Acid Aerosol from the Interaction of the Space Shuttle Rocket Exhaust with the Atmosphere
A description is given of conditions of atmospheric temperature and relative humidity under which hydrochloric acid aerosol is expected upon interaction of the proposed space shuttle rocket exhaust products with the atmosphere.
Rhein, R. A.↗
Site alteration effects from rocket exhaust impingment during a simulated Viking Mars landing. Part 1: Nozzle development and physical site alternation
A potential interference problem for the Viking '75 scientific investigation of the Martian surface resulting from retrorocket exhaust plume impingement of the surface was investigated experimentally and analytically. It was discovered that the conventional bell nozzle originally planned for the Viking Lander retrorockets would produce an unacceptably large amount of physical disturbance to the landing site. An experimental program was subsequently undertaken to find and/or develop a nozzle configuration which would significantly reduce the site alteration. A multiple nozzle configuration, consisting of 18 small bell nozzles, was shown to produce a level of disturbance that was considered by the Viking Lander Science Teams to be acceptable on the basis of results from full-scale tests on simulated Martian soils.
Romine, G. L.↗
Exhaust pressure and density of various pulsed mpd-arc thruster systems
Exhaust flow in a new, 155 cm i.d., vacuum facility was compared with earlier measurements in a small (15.2 cm i.d.) duct. Reductions in post transient impact pressure were about 5:1 in the larger facility. Corresponding reduced electron number densities (approximately 2 x 10 to the 13th power/cucm) were noted. A new, 125 miscrosecond, pulse forming network power source produced no major differences in impact pressure compared to the crowbarred condenser bank used earlier. Comparing a puff gas feed of the arc chamber with a new 10 millisecond steady gas feed also showed no major difference in impact pressure for 125 miscrosecond powering.
Michels, C. J.↗