2 Matching Results

Search Results

Results: 1 - 2
open access

Development of NACA submerged inlets and a comparison with wing leading-edge inlets for a 1/4-scale model of a fighter airplane

Description: Characteristics of NACA submerged duct entries and wing leading-edge inlets designed for a 1/4 scale flow model of a fighter-type airplane powered by a jet engine in the fuselage are presented.
Date: August 7, 1947
Creator: Mossman, Emmet A. & Gault, Donald E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of an Experimental Supersonic Axial-Flow Compressor

Description: An investigation is in progress at the Langley Laboratory of the NACA to explore the possibilities of axial-flow compressors operating with supersonic velocities relative to the blade rows. The first phase of this investigation, a study of supersonic diffusers, has been reported. The second phase, an analysis of supersonic compressors, has also been reported. Preliminary calculations have shown that very high pressure ratios across a stage, together with somewhat increased mass flows, are poss… more
Date: August 7, 1947
Creator: Erwin, John R.; Wright, Linwood C. & Kantrowitz, Arthur
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen