NASA NTRS · 19630003996
PERFORMANCE OF AN INLET HAVING A VARIABLE-ANGLE TWO-DIMENSIONAL COMPRESSION SURFACE AND A FIXED-GEOMETRY SUBSONIC DIFFUSER FOR APPLICATION TO REDUCED ENGINE ROTATIVE SPEEDS- MACH NUMBERS 0.66, 1.5, 1.7, AND 2.0
Abstract
Air inlet for turbojet engines having variable angle two-dimensional compression surface and fixed-geometry subsonic diffuser
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Allen, J. L.. 1958-01-30. PERFORMANCE OF AN INLET HAVING A VARIABLE-ANGLE TWO-DIMENSIONAL COMPRESSION SURFACE AND A FIXED-GEOMETRY SUBSONIC DIFFUSER FOR APPLICATION TO REDUCED ENGINE ROTATIVE SPEEDS- MACH NUMBERS 0.66, 1.5, 1.7, AND 2.0. https://ntrs.nasa.gov/citations/19630003996
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