0.2-scale B-1 External-compression Inlet Verification Model Test at Transonic and Supersonic Mach Numbers PDF Download
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Author: R. C. German
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 340
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Book Description
Author: R. C. German
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 340
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author:
Publisher:
ISBN:
Category : Government reports announcements & index
Languages : en
Pages : 1048
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Book Description
Author: John F. Riddell
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 250
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Book Description
Results are presented of a wind tunnel investigation of a 0.2-scale model of the left-hand dual-inlet air induction system of the B-1 aircraft. The test was conducted at Mach numbers from 0.55 to 2.3 over an angle-of-attack range from -2 to 13 deg and yaw angles of -6 to 6 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion and turbulence index is presented as a function of engine-face mass-flow ratio for various inlet geometries and model attitudes. Generally, increasing angle of attack caused greated decreases in the performance of the inboard inlet at supersonic Mach numbers and of the outboard inlet at subsonic Mach numbers. Noticeable effects occurred when the structural mode control vanes were varied at the subsonic Mach number at low angles of attack and at negative yaw. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 396
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Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1074
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Author: Harvey H. Hubbard
Publisher:
ISBN:
Category : Aerodynamic noise
Languages : en
Pages : 620
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 944
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 396
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Book Description
Author: Thomas R. Yechout
Publisher: AIAA
ISBN: 9781600860782
Category : Aerodynamics
Languages : en
Pages : 666
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Book Description
Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
