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Weinstein, Maynard I

Publications and source records attributed to Weinstein, Maynard I.

7 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1957

Investigation of an Underslung Normal-wedge Inlet at Free-stream Mach Numbers from 1.50 to 1.99

Two normal -wedge-inlet configurations (straight and sweptback splitter plates) were investigated in the Lewis 8- by 6-foot supersonic wind tunnel at Mach numbers of 1.50 to 1.99. Negligible differences occurred in the performances of the two normal-wedge inlets. In comparison with a previously tested scoop inlet, the normal-wedge configuration showed superior thrust-minus-drag characteristics at Mach 1.99. However the scoop inlet was better at Mach numbers of 1.80 and 1.50.

Vargo, Donald J↗
NASA NTRS1952

Performance of supersonic scoop inlets

A brief summary is made of the performance of a series of variable-geometry type scoop inlets investigated at the Lewis Laboratory on a model of the X-3 airplane fuselage. Data are presented for a range of inlet mass-flow ratios over a Mach number range from 0 to 2 and from 0 degrees to 12 degrees angle of attack. Rounded-lip inlets are found to give satisfactory performance to a Mach number of 1.5. Use of sharp rather than blunt lip configurations is shown to provide considerable gains in available thrust at Mach number 2.0 but penalize take-off performance to the extent that auxiliary air intakes may be required. No one inlet type was found to be superior over the entire range of operating variables. Thus, the choice of a specific inlet design will be influenced by structural and mechanical as well as aerodynamic considerations.

DIFFUSERS, SUPERSONIC↗
NASA NTRS1950

Investigation of Perforated Convergent-divergent Diffusers with Initial Boundary Layer

An experimental investigation was made at Mach number 1.90 of the performance of a series of perforated convergent-divergent supersonic diffusers operating with initial boundary layer, which was induced and controlled by lengths of cylindrical inlets affixed to the diffusers. Supercritical mass-flow and peak total-pressure recoveries were decreased slightly by use of the longest inlets (4 inlet diameters in length). Combinations of cylindrical inlets, perforated diffusers, and subsonic diffuser were evaluated as simulated wind tunnels having second throats. Comparisons with noncontracted configurations of similar scale indicated conservatively computed power reductions of 25 percent.

DIFFUSERS, SUPERSONIC↗