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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
Low-Speed Characteristics of a 45 Degree Swept Wing with Leading-Edge Inlets
Memorandum presenting an investigation to determine the low-speed aerodynamic characteristics of a 45 degree swept wing with leading-edge inlets. The wing had a constant chord and completely spanned the wind tunnel. Results regarding surface-pressure characteristics, lift and pitching-moment characteristics, wake-drag characteristics, and internal-flow characteristics are provided.
Date:
August 13, 1951
Creator:
Dannenberg, Robert E.
System:
The UNT Digital Library