NACA Research Memorandums

From Summary: "By application of a hyperbolic approximation to the form of the bow waves caused by blunt leading edges on an infinite cascade of supersonic blades, the approximate losses in relative total pressure due to the external bow-wave system arising from blunt edges and subsonic axial entrance velocities were computed. The losses increase linearly with leading-edge radius for any given relative Mach number. For a relative Mach number of 1.60, leading-edge radii may be approximately 1.5 percent of the normal blade gap with a 1-percent loss of relative total pressure.

NACA Research Memorandums

Report presenting the application of the external-compression principle to a cascade of blades in an attempt to achieve a closer approach to isentropic contraction ratios in supersonic compressor blading. Tests of a rotor designed to incorporate the external-compression principle are provided. Results regarding overall performance, performance at design speed and peak efficiency, off-design performance, and some considerations for future designs are provided

NACA Research Memorandums

Report presenting an analytical study of four combinations of subsonic and supersonic flow in the rotor- and stator-blade passages of axial-flow compressors