Wind Tunnel Tests of a 0.06-scale B-1 Model at Mach Numbers from 0.60 to 1.60 PDF Download
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Author: C. J. Spurlin
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 110
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Book Description
Author: C. J. Spurlin
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 110
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Book Description
Author: C. J. Spurlin
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 52
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Book Description
Author: C. J. Spurlin
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 0
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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: Neil Arthur Zarin
Publisher:
ISBN:
Category : Rockets (Aeronautics)
Languages : en
Pages : 106
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Book Description
Author: F. J. Graham
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 150
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Book Description
Results are presented of a wind tunnel investigation of a 0.1-scale model of the left-hand dual inlet air induction system of the B-1 aircraft. The test was conducted from Mach number 0.55 to 2.2 over an angle-of-attack range from -4 to 13 deg and yaw angles of -8 to 5 deg. Inlet performance in terms of compressor-face total-pressure recovery, total-pressure distortion, and turbulence index is presented as a function of inlet mass-flow ratios for various inlet geometries and model attitudes. The total-pressure recovery of the mixed-compression inlet was very good, but the total-pressure distortion at critical massflow ratios was higher than normally desired for satisfactory turbine engine operation. Best performance was realized with ramp and throat height schedules determined from previous testing. Effects of angle of attack and yaw were seen as general sidewash effects. The addition of canard-type fins had negligible effect on inlet performance. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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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: B. H. Goethert
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 420
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Book Description
Numerous aspects of transonic aerodynamics include wall interference corrections in conventional wind tunnels, subsonic flow in a variety of wind tunnels, and test results from transonic wind tunnels. 1961 edition.
Author: Albin O. Pearson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 20
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Book Description
Author: Marion R. Bottorff
Publisher:
ISBN:
Category : Jet engines
Languages : en
Pages : 66
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Book Description
