Afterbody/nozzle Pressure Distributions of a Twin-tail Twin-engine Fighter with Axisymmetric Nozzles at Mach Numbers from 0.6 to 1.2

Afterbody/nozzle Pressure Distributions of a Twin-tail Twin-engine Fighter with Axisymmetric Nozzles at Mach Numbers from 0.6 to 1.2 PDF Author: David J. Wing
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Category :
Languages : en
Pages : 220

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NASA Technical Paper

NASA Technical Paper PDF Author:
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ISBN:
Category : Science
Languages : en
Pages : 218

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Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
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Category : Aeronautics
Languages : en
Pages : 548

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Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports PDF Author:
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Category : Aeronautics
Languages : en
Pages : 850

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Afterbody/Nozzle Pressure Distributions of a Twin-Tail Twin-Engine Fighter with Axisymmetric Nozzles at Mach Numbers from 0. 6 to 1. 2

Afterbody/Nozzle Pressure Distributions of a Twin-Tail Twin-Engine Fighter with Axisymmetric Nozzles at Mach Numbers from 0. 6 to 1. 2 PDF Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723510533
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Languages : en
Pages : 220

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Distributions of static pressure coefficient over the afterbody and axisymmetric nozzles of a generic, twin-tail twin-engine fighter were obtained in the Langley 16-Foot Transonic Tunnel. The longitudinal positions of the vertical and horizontal tails were varied for a total of six aft-end configurations. Static pressure coefficients were obtained at Mach numbers between 0.6 and 1.2, angles of attack between 0 deg and 8 deg, and nozzle pressure ratios ranging from jet-off to 8. The results of this investigation indicate that the influence of the vertical and horizontal tails extends beyond the vicinity of the tail-afterbody juncture. The pressure distribution affecting the aft-end drag is influenced more by the position of the vertical tails than by the position of the horizontal tails. Transonic tail-interference effects are seen at lower free-stream Mach numbers at positive angles of attack than at an angle of attack of 0 deg. Wing, David J. Langley Research Center NASA-TP-3509, L-17438, NAS 1.60:3509 RTOP 505-59-30-04...

NASA Scientific and Technical Publications

NASA Scientific and Technical Publications PDF Author:
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Category : Aeronautics
Languages : en
Pages : 410

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Effects of Afterbody Boattail Design and Empennage Arrangement on Aeropropulsive Characteristics of a Twin-engine Fighter Model at Transonic Speeds

Effects of Afterbody Boattail Design and Empennage Arrangement on Aeropropulsive Characteristics of a Twin-engine Fighter Model at Transonic Speeds PDF Author: Linda S. Bangert
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Category : Aerodynamics, Transonic
Languages : en
Pages : 140

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Acoustics and Trust of Separate-Flow Exhaust Nozzles With Mixing Devices for High-Bypass-Ratio Engines

Acoustics and Trust of Separate-Flow Exhaust Nozzles With Mixing Devices for High-Bypass-Ratio Engines PDF Author:
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Category :
Languages : en
Pages : 26

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AIAA Journal

AIAA Journal PDF Author: American Institute of Aeronautics and Astronautics
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Category : Aeronautics
Languages : en
Pages : 1252

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NASA SP.

NASA SP. PDF Author:
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Category : Aeronautics
Languages : en
Pages : 396

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