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Evaluation Study of the Oxidation-Corrosion Characteristics of Aircraft Turbine Engine Lubricants. Volume I
Report Number: AFAPL TR 70-10 Volume 1
Author(s): Cuellar, J. P.; Baber, B. B.
Corporate Author: Southwest Research Inst San Antonio TX
Publication Date: 5/1/1970
Pages: 47
Project: 0
Task: 0
AD Number: AD0869884
Abstract Text:
Results of oxidation-corrosion test evaluations on numerous aircraft turbine engine lubricants are given. Lubricant types include those related to four specifications as well as a number of experimental-type fluids such as polyphenyl ethers. Blends of selected lubricants were also examined. Test conditions were varied extensively in the study, with emphasis on the parameters of time, temperature, airflow, metals, and reflux of condensable sample vapors. A major objective in investigations with conventional, ester-type lubricants was a comparison of relative performance for test series of short duration and high temperature versus long duration (26 days) and relatively low temperature. In addition, several experimental-type fluids were evaluated in a test series over a temperature range of 600 to 680F. This investigation was mainly concerned with performance effects due to variation of metal types in the corrosion specimen set. The applicability of electrocleaning of metal specimens was also explored with regard to improvement of the repeatability of corrosion data.
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Evaluation Study of the Oxidation-Corrosion Characteristics of Aircraft Turbine Engine Lubricants. Volume II.
Report Number: AFAPL TR 70-10 Volume 2
Author(s): Cuellar, J. P.; Baber, B. B.
Corporate Author: Southwest Research Inst San Antonio TX
Publication Date: 5/1/1970
Pages: 235
Project: 0
Task: 0
AD Number: AD0869885
Abstract Text:
The report contains a compilation of the individual test data sheets for all tests reported in AD-869 884. The data sheets are presented in the order of test number.
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The NTIS Order Number for this report is: AD869885
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Three-Dimensional Nozzle Design for Maximum Thrust. Volume I. Theoretical Development and Results
Report Number: AFAPL TR 70-79 Volume 1
Author(s): Snyder, Lynn E.; Thompson, H. Doyle
Corporate Author: Purdue University Jet Propulsion Center
Laboratory: Air Force Aero Propulsion Laboratory
Publication Date: 10/28/1970
Pages: 180
Features: + Diagram(s) + Graph(s) + Table(s)
Contract: F33615-67-C-1068
Project: None Given
Task: None Given
AD Number: AD0878642
Photo Enhancement: Not Needed
Abstract Text:
The problem of designing three-dimensional (nonaxisymmetric) supersonic nozzles which produce the maximum axial thrust for a prescribed upstream flow field, mass flow rate, exit lip shape and position, and ambient pressure was formulated and numerically solved. The formulation was written to consider a three-dimensional, supersonic, isoenergetic, homentropic flow of a perfect gas. The axial thrust and mass flow rate were written as integrals over a control surface which was constrained to pass through the exit lip of the nozzle. The functional to be maximized was formed by summing the integral equation for the axial thrust and the integral equation for the mass flow rate times a Lagrange multiplier. The fixed length and fixed ambient pressure constraints were imposed by substitution into the variational problem. The numerical solution technique was programmed for the CDC 6500 computer. The results confirm that the three-dimensional optimal nozzles designed using this technique are significantly better than three-dimensional nozzles that have identical initial conditions and have comparable overall dimensions. Furthermore, the results show that two-dimensional or axisymmetric methods are not adequate for designing three-dimensional optimum nozzles.
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