An Introduction to Thrust-Vectored Aircraft Nozzles
An Introduction to Thrust-Vectored Aircraft Nozzles

Author: Erich Wilson

Publisher: LAP Lambert Academic Publishing

Published: 2013

Total Pages: 308

ISBN-13: 9783659412653

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Thrust-vectoring flight control is a leading-edge technology now being implemented in production aircraft such as the F-22, Su-37 and MiG 35. It significantly increases aircraft maneuverability and capability through enabling the use of jet-deflection as an alternative or enhancement to conventional aircraft flight control. Analytical modeling of thrust-vectoring nozzles has been at best fragmentary in publicly available literature in the past. For robust nozzle modeling not only the internal fluid mechanics need to be considered, but the dynamic geometry of the nozzle as well as the influence on the forces obtained from the jet by the flight velocity and angle of attack of the aircraft. With the fervent research into vertical flight capabilities as in the Joint Strike Fighter program, among other aircraft, the influence of the ground effect on the jet must also be considered. In all of this, the foundation of analysis lies in the understanding and modeling of aircraft nozzle performances; both conventional and thrust-vectored. This book seeks to lay a foundation for such work.

Thrust Vectoring Nozzle for Modern Military Aircraft
Thrust Vectoring Nozzle for Modern Military Aircraft

Author: Daniel Ikaza

Publisher:

Published: 2000

Total Pages: 12

ISBN-13:

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This paper describes the technical features of the Thrust Vectoring Nozzle (TVN) developed by ITP and its advantages for modem military aircraft. It is presented in Conjunction with two other papers by DASA (Thrust Vectoring for Advanced Fighter Aircraft High Angle of Attack Intake Investigations) and MTU-Muenchen (Integrated Thrust Vector Jet Engine Control) respectively.

An Experimental Investigation of Thrust Vectoring Two-Dimensional Convergent-Divergent Nozzles Installed in a Twin-Engine Fighter Model at High Angles of Attack
An Experimental Investigation of Thrust Vectoring Two-Dimensional Convergent-Divergent Nozzles Installed in a Twin-Engine Fighter Model at High Angles of Attack

Author: National Aeronautics and Space Administration (NASA)

Publisher: Createspace Independent Publishing Platform

Published: 2018-07-17

Total Pages: 128

ISBN-13: 9781722936518

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An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine thrust vectoring capability of subscale 2-D convergent-divergent exhaust nozzles installed on a twin engine general research fighter model. Pitch thrust vectoring was accomplished by downward rotation of nozzle upper and lower flaps. The effects of nozzle sidewall cutback were studied for both unvectored and pitch vectored nozzles. A single cutback sidewall was employed for yaw thrust vectoring. This investigation was conducted at Mach numbers ranging from 0 to 1.20 and at angles of attack from -2 to 35 deg. High pressure air was used to simulate jet exhaust and provide values of nozzle pressure ratio up to 9. Capone, Francis J. and Mason, Mary L. and Leavitt, Laurence D. Langley Research Center AIRCRAFT ENGINES; CONVERGENT-DIVERGENT NOZZLES; FIGHTER AIRCRAFT; LONGITUDINAL CONTROL; THRUST VECTOR CONTROL; ANGLE OF ATTACK; FLAPS (CONTROL SURFACES); JET EXHAUST; NOZZLE GEOMETRY; PRESSURE RATIO; RESEARCH AIRCRAFT; WIND TUNNEL TESTS; YAW...

Initial Flight Test Evaluation of the F-15 ACTIVE Axisymmetric Vectoring Nozzle Performance
Initial Flight Test Evaluation of the F-15 ACTIVE Axisymmetric Vectoring Nozzle Performance

Author: John S. Orme

Publisher:

Published: 1998

Total Pages: 26

ISBN-13:

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A full envelope database of a thrust-vectoring axisymmetric nozzle perfomance for the Pratt & Whitney Pitch/Yaw Balance Beam Nozzle (P/YBBN) is being developed using the F-15 Advanced Control Technology for Integrated Vehicles (ACTIVE) aircraft. At this time, flight research has been completed for steady-state pitch vector angles up to 20 deg. at an altitude of 30,000 ft from low power settings to maximum afterburner power. The nozzle performance database includes vector forces, internal nozzle pressures, and temperatures all of which can be used for regression analysis modeling. The database was used to substantiate a set of nozzle performance data from wind tunnel testing and computational fluid dynamic analyses. Findings from initial flight research at Mach 0.9 and 1.2 are presented in this paper. The results show that vector efficiency is strongly influenced by power setting. A significant discrepancy in nozzle performance has been discovered between predicted and measured results during vectoring.