Feasibility study and model development for a ferrofluid viscous damper Final report, 8 Nov. 1966 - 8 Mar. 1967
Development of magnetic fluid viscous oscillation damper for scientific satellites
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Operating and maintenance instructions. Development model non-magnetic flight- type mass spectrometer
Operating and maintenance instructions for experimental nonmagnetic flight mass spectrometer
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Optimized Cost/Performance Design Methodology: Volume 3 - Concept Analysis and Model Development, Book 1 - Concept Analysis
Concept analysis for optimized cost orbital space transportation system
Source record↗
Model development of supersonic trough wind with shocks
The time dependent one dimensional hydrodynamic equations describe the evolution of the thermal plasma flow along closed magnetic field lines outside of the plasmasphere. The convection of the supersonic polar wind onto a closed fieldline results in the assumed formation of collisionless plasma shocks. These shocks move earthward as the field line with its frozen-in plasma remains fixed or contracts with time to smaller L coordinates. The high equatorial plasma temperature (of the order of electron volts) produced by the shock process decreases with time if the flow is isothermal but it will increase if the contraction is under adiabatic conditions. Assuming adiabaticity a peak in the temperature forms at the equator in conjunction with a depression in the ion density. After an initial contraction, if the flux tube drifts to higher L coordinates the direction of the shock motion can be reversed so that the supersonic region will expand along the field line towards the state characterizing the supersonic polar wind. A rapid expansion will lower the equatorial density while the temperature decreases with time under adiabatic but not isothermal conditions.
Grebowsky, J. M.↗
Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development
The analytical effort was directed towards (1) completing the design of the combustor exit instrumentation assembly, (2) analyzing the coolant flow distribution of the cowl leading edge tip section, (3) determining effects of purge gas pressure on AIM performance analysis, and (4) analyzing heat transfer and associated stress problems related to the cowl leading edge tip section and the nozzle shroud assembly for test conditions.
Jilly, L. F.↗
Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development
The analytical effort was directed toward (1) analyzing the latest inputs of possible test conditions and their impact on hardware; (2) review structural capabilities of the AIM unit; (3) analyzing coolant flow paths, heat transfer, and associated problems relative to the cowl leading edge tip section; and (4) redefining requirements of flow-calibrating the air-metering duct.
Jilly, L. F.↗
Hypersonic research engine project. Phase 2: Aerothermodynamic integration model development
The fabrication of the various components of the HRE AIM was completed. The purge system necessary for the cavity bounded by the outer shell assembly and the outer cowl body was studied. Preparations were begun for establishing a format for test data acquisition and reduction.
Jilly, L. F.↗
Model development of supersonic trough wind with shocks.
The time-dependent one dimensional hydrodynamic equations describe the evolution of the thermal plasma flow along closed magnetic field lines outside of the plasmasphere. The convection of the supersonic polar wind onto a closed field line results in the assumed formation of collisionless plasma shocks. These shocks move earthward as the field line with its 'frozen-in' plasma remains fixed or contracts with time to smaller L coordinates. The high equatorial plasma temperature (of the order of electron volts) produced by the shock process decreases with time if the flow is isothermal, but it will increase if the contraction is under adiabatic conditions. Assuming adiabaticity a peak in the temperature forms at the equator in conjunction with a depression in the ion density. After an initial contraction, if the flux tube drifts to higher L coordinates, the direction of the shock motion can be reversed so that the supersonic region will expand along the field line toward the state characterizing the supersonic polar wind.
Grebowsky, J. M.↗
Experiment design session: Wheat yield model development
There are no author-identified significant results in this report.
Sakamoto, C. M.↗
Experiment results session: Accuracy and performance of LACIE crop development models
There are no author-identified significant results in this report.
Woolley, S.↗
Supporting Research and Technology (SRT) session: Status of yield estimation technology, a review of second-generation model development
There are no author-identified significant results in this report.
Stuff, R.↗
Precipitation measurement requirements for general circulation climate model development and applications
Global scale diagnostics, regional diagnostics, and satellite IR data are discussed.
Mintz, Y.↗
Model development and statistical investigation of turbine blade mistuning
This paper discusses the development of an efficient algorithm which calculates the individual blade response of a bladed turbine disk, the subsequent statistical investigation to establish mistuning dependencies, and procedures which reduce the increase in blade amplitudes caused by mistuning.
Griffin, J. H.↗
Thermal barrier coating life prediction model development
Thermal barrier coatings (TBCs) for turbine airfoils in high-performance engines represent an advanced materials technology that has both performance and durability benefits. In order to achieve these benefits, however, the TBC system must be reliable. Prediction of the lives of two types of strain-tolerant and oxidation-resistant TBC systems that are produced by commercial coating suppliers to the gas turbine industry is examined. The plasma sprayed TBC system, composed of a low-pressure plasma spray (LPPS) applied oxidation resistant NiCrAlY bond coating and an air-plasma-sprayed yttria (8 percent) partially stabilized zirconia insulative layer is applied by both Chromalloy and Klock. The second type of TBC is applied by the electron beam-physical vapor depositon (EB-PVD) process by Temescal.
Strangman, T. E.↗
Thermal barrier coating life prediction model development
This program focuses on predicting the lives of two types of strain-tolerant and oxidation-resistant thermal barrier coating (TBC) systems that are produced by commercial coating suppliers to the gas turbine industry. The plasma-sprayed TBC system is composed of a low pressure, plasma sprayed applied, oxidation resistant NiCrAlY bond coating. The other system is an air plasma sprayed yttria (8 percent) partially stabilized zirconia insulative layer.
Strangman, T. E.↗
Thermal barrier coating life prediction model development
Thermal barrier coatings (TBCs) for turbine airfoils in high-performance engines represent an advanced materials technology with both performance and durability benefits. The foremost TBC benefit is the reduction of heat transferred into air-cooled components, which yields performance and durability benefits. This program focuses on predicting the lives of two types of strain-tolerant and oxidation-resistant TBC systems that are produced by commercial coating suppliers to the gas turbine industry. The plasma-sprayed TBC system, composed of a low-pressure plasma-spray (LPPS) or an argon shrouded plasma-spray (ASPS) applied oxidation resistant NiCrAlY (or CoNiCrAlY) bond coating and an air-plasma-sprayed yttria (8 percent) partially stabilized zirconia insulative layer, is applied by Chromalloy, Klock, and Union Carbide. The second type of TBC is applied by the electron beam-physical vapor deposition (EB-PVD) process by Temescal.
T E Strangman↗
Thermal barrier coating life prediction model development
The objectives of this program are to increase understanding of thermal barrier coating (TBC) degradation and failure modes, to generate quantitative ceramic failure life data under cyclic thermal conditions which simulate those encountered in gas turbine engine service, and to develop an analytical methodology for prediction of coating life in the engine. Observations of degradation and failure modes in plasma deposited ceramic indicate that spallation failure results from progressive cracking of the ceramic parallel to and adjacent to, but not coincident with the metal-ceramic interface.
Demasi, J. T.↗
Numerically efficient algorithm for model development of high-order systems
A technique for estimating transfer functions in partial fraction expansion form from frequency response data for a high-order system is presented. The problem formulation avoids many of the numerical difficulties associated with high-order polynomials and has the advantage of having the option to fix the camping and frequency of a mode, if known, during the estimation process. The resulting transfer function(s) may be converted to Jordan-Form time domain equations directly. During the implementation of this technique, a frequency and amplitude normalizing window was developed that maximized the efficiency of the optimization algorithm. The combination of estimating the transfer function in factored form, the ability to fix preciously determined parameters and the effectiveness of the normalizing window led to a progressive approach to synthesizing transfer functions from frequency response data for high-order systems.
Parada, L. O.↗