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  • 1980-1984  (11)
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Year
  • 1
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    Static internal performance of single-expansion-ramp nozzles with thrust-vectoring capability up to 60 deg (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted at static conditions (wind off) in the static-test facility of the Langley 16-Foot Transonic Tunnel. The effects of geometric thrust-vector angle, sidewall containment, ramp curvature, lower-flap lip angle, and ramp length on the internal performance of nonaxisymmetric single-expansion-ramp nozzles were investigated. Geometric thrust-vector angle was varied from -20 deg. to 60 deg., and nozzle pressure ratio was varied from 1.0 (jet off) to approximately 10.0.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2364 , L-15766 , NAS 1.60:2364
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Effects of tail span and empennage arrangement on drag of a typical single-engine fighter aft end (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the Langley 16 foot Transonic Tunnel to determine the effects of tail span and empennage arrangement on drag of a single engine nozzle/afterbody model. Tests were conducted at Mach numbers from 0.50 to 1.20, nozzle pressures frm 1.0 (jet off) to 8.0, and angles of attack from -3 to 9 deg, depending upon Mach numbers. Three empennage arrangements (aft, staggered, and forward) were investigated with several different tail spans. The results of the investigation indicate that tail span and position have a significant effect on the drag at transonic speeds. Unfavorable tail interference was largely due to the outer portion of the tail surfaces. The inner portion near the nozzle and afterbody did little to increase drag other than surface skin friction. Tail positions forward of the nozzle generally had lower tail interference.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2352 , L-15742 , NAS 1.60:2352
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    A static investigation of yaw vectoring concepts on two-dimensional convergent-divergent nozzles (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The flow-turning capability and nozzle internal performance of yaw-vectoring nozzle geometries were tested in the NASA Langley 16-ft Transonic wind tunnel. The concept was investigated as a means of enhancing fighter jet performance. Five two-dimensional convergent-divergent nozzles were equipped for yaw-vectoring and examined. The configurations included a translating left sidewall, left and right sidewall flaps downstream of the nozzle throat, left sidewall flaps or port located upstream of the nozzle throat, and a powered rudder. Trials were also run with 20 deg of pitch thrust vectoring added. The feasibility of providing yaw-thrust vectoring was demonstrated, with the largest yaw vector angles being obtained with sidewall flaps downstream of the nozzle primary throat. It was concluded that yaw vector designs that scoop or capture internal nozzle flow provide the largest yaw-vector capability, but decrease the thrust the most.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1288
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Empennage/afterbody integration for single and twin-engine fighter aircraft (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An extensive experimental program to determine the effects of empennage surfaces on single and twin-engine afterbody/nozzle drag has been conducted by the Propulsion Aerodynamics Branch at the NASA Langley Research Center. Empennage interference drag was obtained by using experimental values of afterbody/nozzle drag and computed values of empennage drag. The effects of tail location, span, number (single versus twin), toe angle, cant angle, camber and root chord length are discussed. The magnitude of empennage interference drag on single and twin engine configurations is examined.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1126
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Investigation of installation effects on twin-engine convergent-divergent nozzles (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine installation effects on convergent-divergent nozzles applicable to twin-engine reduced-power supersonic cruise aircraft. Tests were conducted at Mach numbers from 0.50 to 1.20, angles of attack from -5 deg to 9 deg, and at nozzle pressure ratios from jet off (1.0) to 8.0. The effects of empennage arrangement, nozzle length, and afterbody closure on total and component drag coefficients were investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2205 , L-15609 , NAS 1.60:2205
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Thrust augmented spin recovery device (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Yaw control surfaces were developed for a jet propelled aircraft. A thrust augmented rudder is disposed above the jet exhaust stream and a thrust rudder tab extends downward into the jet exhaust stream. These components are cooperatively deflected to generate yawing moments for directional control of the aircraft.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Investigation of convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted of isolated convergent-divergent nozzles to determine the effect of several design parameters on nozzle performance. Tests were conducted using high pressure air for propulsion simulation at Mach numbers from 0.60 to 2.86 at an angle of attack of 0 deg and at nozzle pressure ratios from jet off to 46.0. Three power settings (dry, partial afterburning, and maximum afterburning), three nozzle lengths, and nozzle expansion ratios from 1.22 to 2.24 were investigated. In addition, the effects of nozzle throat radius and a cusp in the external boattail geometry were studied. The results of this study indicate that, for nozzles operating near design conditions, increasing nozzle length increases nozzle thrust-minus-drag performance. Nozzle throat radius and an external boattail cusp had negligible effects on nozzle drag or internal performance.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1766 , L-13974
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Effect of simulated in-flight thrust reversing on vertical-tail loads of F-18 and F-15 airplane models (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Investigations were conducted in the Langley 16-Foot Transonic Tunnel to provide data on a 0.10-scale model of the prototype F-18 airplane and a 0.047-scale model of the F-15 three-surface configuration (canard, wing, and horizontal tails). Test data were obtained at static conditions and at Mach numbers from 0.6 to 1.2 over an angle-of-attack range from 2 deg to 15 deg. Nozzle pressure ratio was varied from jet off to about 8.0.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1890 , L-14531
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Investigation of axisymmetric and nonaxisymmetric nozzles installed on a 0.10 scale F-18 prototype airplane model (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Langley 16 foot transonic tunnel was used to investigate the afterbody/nozzle longitudinal aerodynamic characteristics of three different two dimensional nozzles and a base-line axisymmetric nozzle installed on a 0.10 scale model of the F-18 airplane. The effects of thrust vectoring and in-flight thrust reversing were also studied. Horizontal-tail deflections of 0 deg, -2 deg, and -5 deg were tested. Test data were obtained at static conditions and at Mach numbers from 0.60 to 1.20 over an angle-of-attack range from -2 deg to 10 deg. Nozzle pressure ratio was varied from jet off to about 10.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1638 , L-13401
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Static internal performance of single expansion-ramp nozzles with thrust vectoring and reversing (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of geometric design parameters on the internal performance of nonaxisymmetric single expansion-ramp nozzles were investigated at nozzle pressure ratios up to approximately 10. Forward-flight (cruise), vectored-thrust, and reversed-thrust nozzle operating modes were investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1962 , L-14902 , NAS 1.60:1962
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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