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  • 1
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    Static internal performance of a thrust vectoring and reversing two-dimensional convergent-divergent nozzle with an aft flap (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The static internal performance of a multifunction nozzle having some of the geometric characteristics of both two-dimensional convergent-divergent and single expansion ramp nozzles has been investigated in the static-test facility of the Langley 16-Foot Transonic Tunnel. The internal expansion portion of the nozzle consisted of two symmetrical flat surfaces of equal length, and the external expansion portion of the nozzle consisted of a single aft flap. The aft flap could be varied in angle independently of the upper internal expansion surface to which it was attached. The effects of internal expansion ratio, nozzle thrust-vector angle (-30 deg. to 30 deg., aft flap shape, aft flap angle, and sidewall containment were determined for dry and afterburning power settings. In addition, a partial afterburning power setting nozzle, a fully deployed thrust reverser, and four vertical takeoff or landing nozzle, configurations were investigated. Nozzle pressure ratio was varied up to 10 for the dry power nozzles and 7 for the afterburning power nozzles.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2549 , L-16025 , NAS 1.60:2549
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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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
  • 3
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    Static internal performance of a single-engine onaxisymmetric-nozzle vaned-thrust-reverser design with thrust modulation capabilities (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted at wind-off conditions in the stati-test facility of the Langley 16-Foot Transonic Tunnel. The tests were conducted on a single-engine reverser configuration with partial and full reverse-thrust modulation capabilities. The reverser design had four ports with equal areas. These ports were angled outboard 30 deg from the vertical impart of a splay angle to the reverse exhaust flow. This splaying of reverser flow was intended to prevent impingement of exhaust flow on empennage surfaces and to help avoid inlet reingestion of exhaust gas when the reverser is integrated into an actual airplane configuration. External vane boxes were located directly over each of the four ports to provide variation of reverser efflux angle from 140 deg to 26 deg (measured forward from the horizontal reference axis). The reverser model was tested with both a butterfly-type inner door and an internal slider door to provide area control for each individual port. In addition, main nozzle throat area and vector angle were varied to examine various methods of modulating thrust levels. Other model variables included vane box configuration (four or six vanes per box), orientation of external vane boxes with respect to internal port walls (splay angle shims), and vane box sideplates. Nozzle pressure ratio was varied from 2.0 approximately 7.0.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2519 , L-15991 , NAS 1.60:2519
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Operating Characteristics of the Multiple Critical Venturi System and Secondary Calibration Nozzles Used for Weight-Flow Measurements in the Langley 16-Foot Transonic Tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted in the Langley 16 Foot Transonic Tunnel to determine the weight flow measurement characteristics of a multiple critical Venturi system and the nozzle discharge coefficient characteristics of a series of convergent calibration nozzles. The effects on model discharge coefficient of nozzle throat area, model choke plate open area, nozzle pressure ratio, jet total temperature, and number and combination of operating Venturis were investigated. Tests were conducted at static conditions (tunnel wind off) at nozzle pressure ratios from 1.3 to 7.0.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86405 , L-15960 , NAS 1.15:86405
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Advanced technology exhaust nozzle development (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The requirement for greater tactical aircraft operational capabilities has led to increasing research emphasis on the refinement of engine/airframe integration methods and exhaust nozzle flexibility. A major prospective advancement in the development of these capabilities takes the form of multifunctional exhaust nozzle systems with thrust reversal and thrust vectoring features, whose operation will be shared by both airframe and powerplant control systems. Attention is presently given to the two-dimensional convergent-divergent and single expansion ramp nozzle designs, with emphasis on the variable geometry mechanical systems by which they assume cruising flight, vectoring, and thrust reversal operations. The nozzles have been wind tunnel model-tested for the cases of the F-18 fighter and a supersonic cruise configuration concept.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1286
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Static internal performance including thrust vectoring and reversing of two-dimensional convergent-divergent nozzles (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of geometric design parameters on two dimensional convergent-divergent nozzles were investigated at nozzle pressure ratios up to 12 in the static test facility. Forward flight (dry and afterburning power settings), vectored-thrust (afterburning power setting), and reverse-thrust (dry power setting) nozzles were investigated. The nozzles had thrust vector angles from 0 deg to 20.26 deg, throat aspect ratios of 3.696 to 7.612, throat radii from sharp to 2.738 cm, expansion ratios from 1.089 to 1.797, and various sidewall lengths. The results indicate that unvectored two dimensional convergent-divergent nozzles have static internal performance comparable to axisymmetric nozzles with similar expansion ratios.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2253 , L-15671 , NAS 1.60:2253
    Format: application/pdf
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  • 7
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    Static internal performance of single-expansion-ramp nozzles with various combinations of internal geometric parameters (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of five geometric design parameters on the internal performance of single-expansion-ramp nozzles were investigated at nozzle pressure ratios up to 10 in the static-test facility of the Langley 16-Foot Transonic Tunnel. The geometric variables on the expansion-ramp surface of the upper flap consisted of ramp chordal angle, ramp length, and initial ramp angle. On the lower flap, the geometric variables consisted of flap angle and flap length. Both internal performance and static-pressure distributions on the centerlines of the upper and lower flaps were obtained for all 43 nozzle configurations tested.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86270 , L-15814 , NAS 1.15:86270
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Stability and control characteristics of a three-surface advanced fighter configuration at angles of attack up to 45 deg (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The tests were conducted at Mach numbers from 0.40 to 0.90, at angles of attack up to 45 deg for the lower Mach numbers, and at angles of sideslip up to 15 deg. The model variations under study included adding a canard surface and deflecting horizontal tails, ailerons, and rudders.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83171 , L-14433
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Static internal performance characteristics of two thrust reverser concepts for axisymmetric nozzles (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The statis performance of two axisymmetric nozzle thrust reverser concepts was investigated. A rotating vane thrust reverser represented a concept in which reversing is accomplished upstream of the nozzle throat, and a three door reverser concept provided reversing downstream of the nozzle throat. Nozzle pressure ratio was varied from 2.0 to approximately 6.0. The results of this investigation indicate that both the rotating vane and three door reverser concepts were effective static thrust spoilers with the landing approach nozzle geometry and were capable of providing at least a 50 percent reversal of static thrust when fully deployed with the ground roll nozzle geometry.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2025 , NAS 1.60:2025
    Format: application/pdf
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  • 10
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    Performance characteristics of axisymmetric convergent-divergent exhaust nozzles with longitudinal slots in the divergent (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the Langley 16 foot Transonic Tunnel and in the static test facility of that tunnel to determine the effects of divergent flap ventilation of an axisymmetric nozzle on nozzle internal (static) and wind on performance. Tests were conducted at 0 deg angle of attack at static conditions and at Mach numbers from 0.6 to 1.2. Ratios of jet total pressure to free stream static pressure were varied from 1.0 (jet off) to approximately 14.0 depending on Mach number. The results of this study indicate that divergent flap ventilation generally provided large performance benefits at overexpanded nozzle conditions and performance reductions at underexpanded nozzle conditions when compared to the baseline (unventilated) nozzles. Ventilation also reduced the peak static and wind on performance levels.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2013 , L-15119 , NAS 1.60:2013
    Format: application/pdf
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