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Performance of an All-Internal Conical Compression Inlet with Annular Throat Bleed at Mach Number 5.0
From Summary: "An all-internal conical compression inlet with annular bleed at the throat was investigated at Mach 5.0 and zero angle of attack. The minimum contraction ratio of the supersonic diffuser, coincident with a mass-flow ratio of 1.0, was determined to be 0.084 as compared with the isentropic contraction ratio of 0.04 at Mach 5.0. The over-all inlet performance was very sensitive to the amount of annular bleed at the throat because of the extensive boundary layer."
Date:
August 6, 1958
Creator:
Stitt, Leonard E. & Obery, Leonard J.
System:
The UNT Digital Library
Experimental and theoretical study of the interference at low speed between slender bodies and triangular wings
Report presenting the aerodynamic characteristics of several wing-fuselage combinations measured at a Mach number of 0.25. Each combination consisted of a triangular wing with an aspect ratio of 2.0 and body of revolution with a fineness ratio of 12.5. Results regarding wings in the presence of bodies, wing-body combinations, and dorsal fins are provided.
Date:
May 6, 1953
Creator:
Hopkins, Edward J. & Carel, Hubert C.
System:
The UNT Digital Library