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open access

Lift, drag and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds: Plane tapered wing of aspect ratio 3.1 with 3-percent-thick rounded-nose section

Description: Report presenting a wing-body combination with a plane tapered wing of aspect ratio 3.1, taper ratio of 0.39, and 3-percent-thick, rounded-nose sections in streamwise planes at subsonic and supersonic Mach numbers. The lift, drag, and pitching moment are presented for a range of Mach numbers and Reynolds numbers.
Date: July 9, 1952
Creator: Heitmeyer, John C.
open access

Over-all performance of the J71 three-stage turbine

Description: Report presenting an investigation to determine the overall performance of the three-stage turbine from the J71 turbojet engine. The turbine operated with a maximum brake internal efficiency of approximately 0.84 at an equivalent overall pressure ratio of approximately 3.6 and an equivalent rotor speed of about 110 percent of the equivalent design value.
Date: July 9, 1952
Creator: Berkey, William E.
open access

An analysis of the potentialities of a two-stage counterrotating supersonic compressor

Description: From Introduction: "The supersonic axial-flow compressor, for example, appears to offer advantages of high stage pressure ratio and height weight flows (reference 1) but problems peculiar to this compressor type have accompanied its introduction. For high single-stage pressure ratios (>4) the problem of converting the high dynamic energy to useful pressure arises (reference 2). In addition, the high tip speeds and weight flows combine to create a difficult situation for the turbine designer."
Date: July 9, 1952
Creator: Wilcox, Ward W.
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