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  • 1
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    Static Investigation of a Multiaxis Thrust-Vectoring Nozzle With Variable Internal Contouring Ability (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The thrust efficiency and vectoring performance of a convergent-divergent nozzle were investigated at static conditions in the model preparation area of the Langley 16-Foot Transonic Tunnel. The diamond-shaped nozzle was capable of varying the internal contour of each quadrant individually by using cam mechanisms and retractable drawers to produce pitch and yaw thrust vectoring. Pitch thrust vectoring was achieved by either retracting the lower drawers to incline the throat or varying the internal flow-path contours to incline the throat. Yaw thrust vectoring was achieved by reducing flow area left of the nozzle centerline and increasing flow area right of the nozzle centerline; a skewed throat deflected the flow in the lateral direction.
    Keywords: Aerodynamics
    Type: NASA-TP-3628 , NAS 1.60:3628 , L-17570
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Static Thrust and Vectoring Performance of a Spherical Convergent Flap Nozzle with a Nonrectangular Divergent Duct (1998)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The static internal performance of a multiaxis-thrust-vectoring, spherical convergent flap (SCF) nozzle with a non-rectangular divergent duct was obtained in the model preparation area of the Langley 16-Foot Transonic Tunnel. Duct cross sections of hexagonal and bowtie shapes were tested. Additional geometric parameters included throat area (power setting), pitch flap deflection angle, and yaw gimbal angle. Nozzle pressure ratio was varied from 2 to 12 for dry power configurations and from 2 to 6 for afterburning power configurations. Approximately a 1-percent loss in thrust efficiency from SCF nozzles with a rectangular divergent duct was incurred as a result of internal oblique shocks in the flow field. The internal oblique shocks were the result of cross flow generated by the vee-shaped geometric throat. The hexagonal and bowtie nozzles had mirror-imaged flow fields and therefore similar thrust performance. Thrust vectoring was not hampered by the three-dimensional internal geometry of the nozzles. Flow visualization indicates pitch thrust-vector angles larger than 10' may be achievable with minimal adverse effect on or a possible gain in resultant thrust efficiency as compared with the performance at a pitch thrust-vector angle of 10 deg.
    Keywords: Aerodynamics
    Type: NASA/TP-1998-206912 , NAS 1.60:206912 , L-17635
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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 (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: 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.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3509 , L-17438 , NAS 1.60:3509
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Fluidic Thrust Vectoring of an Axisymmetric Exhaust Nozzle at Static Conditions (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A sub-scale experimental static investigation of an axisymmetric nozzle with fluidic injection for thrust vectoring was conducted at the NASA Langley Jet Exit Test Facility. Fluidic injection was introduced through flush-mounted injection ports in the divergent section. Geometric variables included injection-port geometry and location. Test conditions included a range of nozzle pressure ratios from 2 to 10 and a range of injection total pressure ratio from no-flow to 1.5. The results indicate that fluidic injection in an axisymmetric nozzle operating at design conditions produced significant thrust-vector angles with less reduction in thrust efficiency than that of a fluidically-vectored rectangular jet. The axisymmetric geometry promoted a pressure relief mechanism around the injection slot, thereby reducing the strength of the oblique shock and the losses associated with it. Injection port geometry had minimal effect on thrust vectoring.
    Keywords: Aircraft Design, Testing and Performance
    Type: DWSAM97-3228 , 1997 ASME Fluids Engineering Division Summer Meeting (FEDSM''97); Jun 22, 1997 - Jun 26, 1997; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Jet-Engine Exhaust Nozzle With Thrust-Directing Flaps (1996)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Convergent/divergent jet-engine exhaust nozzle has cruciform divergent passage containing flaps that move to deflect flow of exhaust in either or both planes perpendicular to main fore-and-aft axis of undeflected flow. Prototype of thrust-vector-control nozzles installed in advanced, high-performance airplanes to provide large pitching (usually, vertical) and yawing (usually, horizontal) attitude-control forces independent of attitude-control forces produced by usual aerodynamic control surfaces.
    Keywords: MACHINERY
    Type: LAR-14692 , NASA Tech Briefs (ISSN 0145-319X); 20; 1; P. 74
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Airborne Separation Assurance and Traffic Management: Research of Concepts and Technology (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: To support the need for increased flexibility and capacity in the future National Airspace System, NASA is pursuing an approach that distributes air traffic separation and management tasks to both airborne and ground-based systems. Details of the distributed operations and the benefits and technical challenges of such a system are discussed. Technology requirements and research issues are outlined, and NASA s approach for establishing concept feasibility, which includes development of the airborne automation necessary to support the concept, is described.
    Keywords: Research and Support Facilities (Air)
    Type: AIAA Paper 99-3989
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Development of a Free-Flight Simulation Infrastructure (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: In anticipation of a projected rise in demand for air transportation, NASA and the FAA are researching new air-traffic-management (ATM) concepts that fall under the paradigm known broadly as ":free flight". This paper documents the software development and engineering efforts in progress by Seagull Technology, to develop a free-flight simulation (FFSIM) that is intended to help NASA researchers test mature-state concepts for free flight, otherwise referred to in this paper as distributed air / ground traffic management (DAG TM). Under development is a distributed, human-in-the-loop simulation tool that is comprehensive in its consideration of current and envisioned communication, navigation and surveillance (CNS) components, and will allow evaluation of critical air and ground traffic management technologies from an overall systems perspective. The FFSIM infrastructure is designed to incorporate all three major components of the ATM triad: aircraft flight decks, air traffic control (ATC), and (eventually) airline operational control (AOC) centers.
    Keywords: Computer Programming and Software
    Type: AIAA Paper 99-4193
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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