Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723184185
Category :
Languages : en
Pages : 130
Book Description
The internal performance of an axisymmetric convergent-divergent nozzle and a nonaxisymmetric convergent-divergent nozzle, both of which utilized a gimbal type mechanism for thrust vectoring was evaluated in the Static Test Facility of the Langley 16-Foot Transonic Tunnel. The nonaxisymmetric nozzle used the gimbal concept for yaw thrust vectoring only; pitch thrust vectoring was accomplished by simultaneous deflection of the upper and lower divergent flaps. The model geometric parameters investigated were pitch vector angle for the axisymmetric nozzle and pitch vector angle, yaw vector angle, nozzle throat aspect ratio, and nozzle expansion ratio for the nonaxisymmetric nozzle. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 2.0 to approximately 12.0. Berrier, Bobby L. and Taylor, John G. Langley Research Center CONVERGENT-DIVERGENT NOZZLES; GIMBALS; NOZZLE EFFICIENCY; NOZZLE GEOMETRY; THRUST VECTOR CONTROL; ASPECT RATIO; PERFORMANCE TESTS; PITCH (INCLINATION); WIND TUNNEL TESTS; YAW...
Internal Performance of Two Nozzles Utilizing Gimbal Concepts for Thrust Vectoring
Author: Bobby L. Berrier
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 136
Book Description
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 136
Book Description
Internal Performance of Two Nozzles Utilizing Gimbal Concepts for Thrust Vectoring
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723184185
Category :
Languages : en
Pages : 130
Book Description
The internal performance of an axisymmetric convergent-divergent nozzle and a nonaxisymmetric convergent-divergent nozzle, both of which utilized a gimbal type mechanism for thrust vectoring was evaluated in the Static Test Facility of the Langley 16-Foot Transonic Tunnel. The nonaxisymmetric nozzle used the gimbal concept for yaw thrust vectoring only; pitch thrust vectoring was accomplished by simultaneous deflection of the upper and lower divergent flaps. The model geometric parameters investigated were pitch vector angle for the axisymmetric nozzle and pitch vector angle, yaw vector angle, nozzle throat aspect ratio, and nozzle expansion ratio for the nonaxisymmetric nozzle. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 2.0 to approximately 12.0. Berrier, Bobby L. and Taylor, John G. Langley Research Center CONVERGENT-DIVERGENT NOZZLES; GIMBALS; NOZZLE EFFICIENCY; NOZZLE GEOMETRY; THRUST VECTOR CONTROL; ASPECT RATIO; PERFORMANCE TESTS; PITCH (INCLINATION); WIND TUNNEL TESTS; YAW...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723184185
Category :
Languages : en
Pages : 130
Book Description
The internal performance of an axisymmetric convergent-divergent nozzle and a nonaxisymmetric convergent-divergent nozzle, both of which utilized a gimbal type mechanism for thrust vectoring was evaluated in the Static Test Facility of the Langley 16-Foot Transonic Tunnel. The nonaxisymmetric nozzle used the gimbal concept for yaw thrust vectoring only; pitch thrust vectoring was accomplished by simultaneous deflection of the upper and lower divergent flaps. The model geometric parameters investigated were pitch vector angle for the axisymmetric nozzle and pitch vector angle, yaw vector angle, nozzle throat aspect ratio, and nozzle expansion ratio for the nonaxisymmetric nozzle. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 2.0 to approximately 12.0. Berrier, Bobby L. and Taylor, John G. Langley Research Center CONVERGENT-DIVERGENT NOZZLES; GIMBALS; NOZZLE EFFICIENCY; NOZZLE GEOMETRY; THRUST VECTOR CONTROL; ASPECT RATIO; PERFORMANCE TESTS; PITCH (INCLINATION); WIND TUNNEL TESTS; YAW...
NASA Technical Paper
Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 432
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 432
Book Description
NASA Technical Paper
Static Internal Performance of a Single Expansion Ramp Nozzle with Multiaxis Thrust Vectoring Capability
NASA Technical Memorandum
Static Performance Investigation of a Skewed-throat Multiaxis Thrust-vectoring Nozzle Concept
Static Internal Performance of a Two-dimensional Convergent Nozzle with Thrust-vectoring Capability Up to 600
Scientific and Technical Aerospace Reports
Static Internal Performance of a Two-dimensional Convergent-divergent Nozzle with Thrust Vectoring
Author: E. Ann Bare
Publisher:
ISBN:
Category : Jet nozzles
Languages : en
Pages : 120
Book Description
Publisher:
ISBN:
Category : Jet nozzles
Languages : en
Pages : 120
Book Description