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Component and over-all performance evaluation of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers
Report presenting an investigation in an altitude test chamber to evaluate the performance of an axial-flow turbojet engine over a range of engine-inlet Reynolds numbers. Reducing the engine inlet Reynolds number resulted in a reduction of corrected air flow and compressor efficiency but did not affect the compressor pressure ratio at a given corrected engine speed.
Date:
July 10, 1952
Creator:
Walker, Curtis L.; Huntley, S. C. & Braithwaite, W. M.
System:
The UNT Digital Library
Effect of trailing edge thickness on lift at supersonic velocities
Report presenting measurements of lift made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. Experiments were conducted at a range of Mach numbers, Reynolds numbers, and wings with and without boundary-layer trips. Results regarding a comparison of experimental results with theory at moderate supersonic Mach numbers and calculations for hypersonic Mach numbers are provided.
Date:
July 10, 1952
Creator:
Chapman, Dean R. & Kester, Robert H.
System:
The UNT Digital Library
Survey of some preliminary investigations of supersonic diffusers at high Mach numbers
From Introduction: "Design studies of long-range supersonic missiles indicate the Mach number range of 3 to 4 to be of considerable promise. Accordingly, the NACA is conducting research on the performance of a wide variety of supersonic diffusers in this range. The initial phase of this research is concerned primarily with the characteristics of conventional axially symmetric diffusers operating at design values of flight Mach number."
Date:
July 10, 1952
Creator:
Cortright, Edgar M., Jr. & Connors, James F.
System:
The UNT Digital Library
Solubility of water in hydrocarbons
Report presenting a study of the literature data on the solubility of water in hydrocarbons, which includes information about the log of solubility, critical solution temperature, and ratios that may affect solubility are provided. An equation is presented and applied to a few petroleum fractions ranging from gasoline to lubricating oil, and a comparison of calculated and experimental solubilities is provided.
Date:
July 10, 1952
Creator:
Hibbard, R. R. & Schalla, R. L.
System:
The UNT Digital Library