Technology\u27s Role in Home Energy Conservation

The technology of space-related advances in miniaturized electronics is being transferred to today\u27s problems in residential energy monitoring. In addition, instrumentation techniques such as infrared scanning and gas leakage detection have been shown to translate into valuable analysis tools in a House Doctor Kit. Long term trends in future housing are viewed in the light of a space capsule environment in which air and energy needs are taken into careful account

Nonlinear Aspects of Combustion Instability in Liquid Propellant Rocket Motors. Second Yearly Progress Report for the Period 1 June 1961 to 31 May 1962

Combustion instability in liquid-propellant rocket engine

Fluid mechanics approach to acoustic liner design

Fluid mechanics approach to acoustic liner desig

High speed hydrogen/graphite interaction

Various aspects of a research program on high speed hydrogen/graphite interaction are presented. Major areas discussed are: (1) theoretical predictions of hydrogen/graphite erosion rates; (2) high temperature, nonequilibrium hydrogen flow in a nozzle; and (3) molecular beam studies of hydrogen/graphite erosion

Nonlinear Aspects of Combustion Instability in Liquid Propellant Rocket Motors Sixth Yearly Progress Report, 1 Jun. 1965 - 31 May 1966

Nonlinear aspects of combustion instability in liquid propellant rocket motor

Combustion contribution to noise in jet engines

The relative importance of combustion as a source of noise in a flow regime representative of a subsonic jet engine exhaust was investigated. The combustion noise source characteristics were obtained from pressure and temperature fluctuation measurements in the combustor and exhaust nozzle. The similarity between the fluctuations in this source region and the far field noise were compared. In the jet exhaust velocity range between 450 and 660 ft/sec investigated in detail, the frequencies of dominant pressure and temperature fluctuations in the combustor were also the frequencies of the dominant far field noise. The overall noise levels were 14 to 20 dB higher than from a corresponding clean jet in the same velocity range. Thus it seemed clear that the unsteadiness associated with the combustion process was responsible for the dominant noise in the far field. A simple analysis to predict the far field noise due to the internal pressure fluctuations causing exit plane velocity fluctuations produced trends closely resembling the measured results, but under predicted the far field noise over the spectral range examined. The possible reason for the higher far field noise is direct transmission of acoustic waves through the nozzle, which was not accounted for in the prediction scheme

Combustion instability research Summary report, 1970

Combustion instability in liquid rocket engine

Summary of combustion instability research at Princeton University, 1969

Control and causes of combustion instability in rocket engine

HEAT TRANSFER IN OSCILLATING FLOW. Second Progress Report for the Period October 1, 1959-September 30, 1960. Aeronautical Engineering Report No. 483-b

The investigation of heat transfer in oscillating flow was continued. A series of tests to further investigate the dependence of heat transfer on various parameters was made for three locations of the heat-transfer section along the duct at several harmonic frequencies with pressure amplitudes varying from 0.4 steady-state pressure to zero. (W.L.H.

HEAT TRANSFER IN OSCILLATING FLOW. Aeronautical Engineering Report No. 483-e, June 30, 1963

Pressure oscillations imposed upon a compressible fluid flowing in a duct produce a substandtial increase of heat transfer between the heated duct wall and the fluid. An experimental investigation was made of the causes of this increase. Resonant conditions in a duct were used to achieve increased oscillating amplitudes. The local heat transfer incresse was found to be highly dependent on the amplitude of the local velocity oscillations, and to depend also on the frequency of oscillations and the duct steadystate pressure and Mach number. The presence of flow reversal further increased the observed heat transfer