Experimental and Analytical Investigation of Axisymmetric Supersonic Cruise Nozzle Geometry at Mach Numbers Form 0.60 to 1.30 PDF Download
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Author: George T. Carson
Publisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 96
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Author: George T. Carson
Publisher:
ISBN:
Category : Supersonic nozzles
Languages : en
Pages : 96
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 96
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 410
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Author: Richard J. Re
Publisher:
ISBN:
Category : Mach number
Languages : en
Pages : 202
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Book Description
Investigations have been conducted in the Langley 16-Foot Transonic Tunnel (at Mach numbers from 0.60 to 1.25) and in the Langley Unitary Plan Winf Tunnel (at Mach numbers from 2.16 to 2.86) at an angle of attack of O° to determine the isolated performane of several expendable nozzle concepts for supersonic noaugmented turbojet applications. The effects of centerbody base shape, shroud length, shroud ventilation, cruciform shroud expansion ration, and cruciform shroud flap vectoring were investigated. The nozzle pressure ration range, which was a function of Mach number, was between 1.9 and 11.8 in the 16-Foot Transonic Tunnel and between 7.9 and 54.9 in the Unitary Plan WInd Tunnel. Discharge coefficient, thrust-minus-drag, and the forces and moments generated by vectoring the divergent shroud flaps (for Mach numbers of 0.60 to 1.25 only) of a cruciform nozzle configuration were measured.
Author: Donald L. Weiss
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 396
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 396
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Author: Allan R. Bishop
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
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Book Description
A computer program previously developed to analyze three-dimensional supersonic nozzles by the method of characteristics has been modified to study less restrictive nozzle geometries and nonuniform inlet conditions. An example indicates that a one-dimensional calculation that uses an averaged initial profile may be significantly in error. A comparison between the analysis and the data from a three-dimensional experiment shows generally good agreement between the two.
Author: Robert J. Cresci
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 74
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Author: Lowell E. Hasel
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 58
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