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  • 1
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    Aerodynamic effects of distributed spanwise blowing on a fighter configuration (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 673-679
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Wind tunnel results of the high-speed NLF(1)-0213 airfoil (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Wind tunnel tests were conducted to evaluate a natural laminar flow airfoil designed for the high speed jet aircraft in general aviation. The airfoil, designated as the High Speed Natural Laminar Flow (HSNLF)(1)-0213, was tested in two dimensional wind tunnels to investigate the performance of the basic airfoil shape. A three dimensional wing designed with this airfoil and a high lift flap system is also being evaluated with a full size, half span model.
    Keywords: AERODYNAMICS
    Type: Research in Natural Laminar Flow and Laminar-Flow Control, Part 3; p 697-726
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flow field over the wing of a delta-wing fighter model with vortex control devices at Mach 0.6 to 1.2 (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of a cooperative research program between NASA, McDonnell Douglas Corporation, and Wright Research and Development Center, a flow field investigation was conducted on a 7.52 percent scale windtunnel model of an advanced fighter aircraft design. The investigation was conducted in the Langley 16 ft Transonic Tunnel at Mach numbers of 0.6, 0.9, and 1.2. Angle of attack was varied from -4 degrees to 30 degrees and the model was tested at angles of sideslip of 0, 5, and -5 degrees. Data for the over the wing flow field were obtained at four axial survey stations by the use of six 5 hole conical probes mounted on a survey mechanism. The wing leading edge primary vortex exerted the greatest influence in terms of total pressure loss on the over the wing flow field in the area surveyed. A number of vortex control devices were also investigated. They included two different apex flaps, wing leading edge vortex flaps, and small large wing fences. The vortex flap and both apex flaps were beneficial in controlling the wing leading edge primary vortex.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4296 , L-16834 , NAS 1.15:4296
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Static internal performance of a two-dimensional convergent-divergent nozzle with thrust vectoring (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A parametric investigation of the static internal performance of multifunction two-dimensional convergent-divergent nozzles has been made in the static test facility of the Langley 16-Foot Transonic Tunnel. All nozzles had a constant throat area and aspect ratio. The effects of upper and lower flap angles, divergent flap length, throat approach angle, sidewall containment, and throat geometry were determined. All nozzles were tested at a thrust vector angle that varied from 5.60 tp 23.00 deg. The nozzle pressure ratio was varied up to 10 for all configurations.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2721 , L-16240 , NAS 1.60:2721
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Effects of afterbody boattail design and empennage arrangement on aeropropulsive characteristics of a twin-engine fighter model at transonic speeds (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of empennage arrangement and afterbody boattail design of nonaxisymmetric nozzles on the aeropropulsive characteristics of a twin-engine fighter-type model have been determined in an investigation conducted in the Langley 16-Foot Transonic Tunnel. Three nonaxisymmetric and one twin axisymmetric convergent-divergent nozzle configurations were tested with three different tail arrangements: a two-tail V-shaped arrangement; a staggered, conventional three-tail arrangement; and a four-tail arrangement similar to that on the F-18. Two of the nonaxisymmetric nozzles were also vectorable. Tests were conducted at Mach numbers from 0.60 to 1.20 over an angle-of-attack range from -3 deg to 9 deg. Nozzle pressure ratio was varied from 1 (jet off) to approximately 12, depending on Mach number. Results indicate that at design nozzle pressure ratio, the medium aspect ratio nozzle (with equal boattail angles on the nozzle sidewalls and upper and lower flaps) had the lowest zero angle of attack drag of the nonaxisymmetric nozzles for all tail configurations at subsonic Mach numbers. The drag levels of the twin axisymmetric nozzles were competitive with those of the medium-aspect-ratio nozzle at subsonic Mach number.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2704 , L-16227 , NAS 1.60:2704
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Wind-tunnel free-flight investigation of a supersonic persistence fighter (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind-tunnel free-flight tests have been conducted in the Langley 30- by 60-Foot Wind Tunnel to examine the high-angle-of-attack stability and control characteristics and control law design of a supersonic persistence fighter (SSPF) at 1 g flight conditions. In addition to conventional control surfaces, the SSPF incorporated deflectable wingtips (tiperons) and pitch and yaw thrust vectoring. A direct eigenstructure assignment technique was used to design control laws to provide good flying characteristics well into the poststall angle-of-attack region. Free-flight tests indicated that it was possible to blend effectively conventional and unconventional control surfaces to achieve good flying characteristics well into the poststall angle-of-attack region.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3258 , L-17040 , NAS 1.60:3258
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Low-speed static and dynamic force tests of a generic supersonic cruise fighter configuration (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Static and dynamic force tests of a generic fighter configuration designed for sustained supersonic flight were conducted in the Langley 30- by 60-foot tunnel. The baseline configuration had a 65 deg arrow wing, twin wing mounted vertical tails and a canard. Results showed that control was available up to C sub L,max (maximum lift coefficient) from aerodynamic controls about all axes but control in the pitch and yaw axes decreased rapidly in the post-stall angle-of-attack region. The baseline configuration showed stable lateral-directional characteristics at low angles of attack but directional stability occurred near alpha = 25 deg as the wing shielded the vertical tails. The configuration showed positive effective dihedral throughout the test angle-of-attack range. Forced oscillation tests indicated that the baseline configuration had stable damping characteristics about the lateral-directional axes.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4138 , L-16599 , NAS 1.15:4138
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Full-scale semispan tests of a business-jet wing with a natural laminar flow airfoil (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A full-scale semispan model was investigated to evaluate and document the low-speed, high-lift characteristics of a business-jet class wing that utilized the HSNLF(1)-0213 airfoil section and a single-slotted flap system. Also, boundary-layer transition effects were examined, a segmented leading-edge droop for improved stall/spin resistance was studied, and two roll-controlled devices were evaluated. The wind-tunnel investigation showed that deployment of single-slotted, trailing-edge flap was effective in providing substantial increments in lift required for takeoff and landing performance. Fixed-transition studies to investigate premature tripping of the boundary layer indicated no adverse effects in lift and pitching-moment characteristics for either the cruise or landing configuration. The full-scale results also suggested the need to further optimize the leading-edge droop design that was developed in the subscale tests.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3133 , L-16905 , NAS 1.60:3133
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Wind-tunnel static and free-flight investigation of high-angle-of-attack stability and control characteristics of a model of the EA-6B airplane (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the Langley 30- by 60-Foot Tunnel and the Langley 12-Foot Low-Speed Tunnel to identify factors contributing to a directional divergence at high angles of attack for the EA-6B airplane. The study consisted of static wind-tunnel tests, smoke and tuft flow-visualization tests, and free-flight tests of a 1/8.5-scale model of the airplane. The results of the investigation indicate that the directional divergence of the airplane is brought about by a loss of directional stability and effective dihedral at high angles of attack. Several modifications were tested that significantly alleviate the stability problem. The results of the free-flight study show that the modified configuration exhibits good dynamic stability characteristics and could be flown at angles of attack significantly higher than those of the unmodified configuration.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3194 , L-16813 , NAS 1.60:3194
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    An analysis for high speed propeller-nacelle aerodynamic performance prediction. Volume 2: User's manual (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A user's manual for the computer program developed for the prediction of propeller-nacelle aerodynamic performance reported in, An Analysis for High Speed Propeller-Nacelle Aerodynamic Performance Prediction: Volume 1 -- Theory and Application, is presented. The manual describes the computer program mode of operation requirements, input structure, input data requirements and the program output. In addition, it provides the user with documentation of the internal program structure and the software used in the computer program as it relates to the theory presented in Volume 1. Sample input data setups are provided along with selected printout of the program output for one of the sample setups.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4199-VOL-2 , E-4399 , NAS 1.26:4199-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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