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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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    Innovative control concepts and component integration for a generic supercruise fighter (1990)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The results of a series of low speed wind tunnel tests conducted in the NASA Langley Research Center (LaRC) 12 ft Low Speed Wind Tunnel (LSWT) are highlighted. The main objectives of the tests were to provide generalized component integration guidelines and to investigate a variety of innovative control concepts designed to improve the high angle of attack (AOA) controllability of a generic class of supercruise fighters.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AGARD, Aerodynamics of Combat Aircraft Controls and of Ground Effects; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Evaluation of the Low-Speed Stability and Control Characteristics of a Mach 5.5 Waverider Concept (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Static force and moment tests of a 0.062-scale model of a hypersonic vehicle study concept known as the LOFLYTE(TM) configuration were conducted in the Langley 12-Foot Low-Speed Tunnel. These tests looked primarily at the low-speed static stability and control characteristics of this configuration. Data were obtained over an angle-of-attack range of -5 deg. to 22 deg. at sideslip angles that ranged between -10 deg. and 10 deg. The tiperons were sized to provide enough pitch control to trim the vehicle up to alpha = 16 deg. with no more than 10 deg. of surface deflection and data obtained in this test showed that 10 deg. of tiperon deflection was nearly sufficient to trim the configuration up to the desired angle of attack. Because of the pitching-moment characteristics of the LOFLYTE(TM) configuration, there is a reasonably high level of unpowered trimmed lift at nominal takeoff and approach to landing that should allow for acceptable takeoff and landing speeds for this vehicle. Initial evaluation of the directional stability characteristics of this configuration showed a significant instability between alpha = 10 deg. and about alpha = 18 deg. This test determined that the cause of this instability was the interaction of the wing leading-edge vortex with the vertical tails. Moving the vertical tails either inboard or outboard from the baseline location eliminated this unfavorable interaction.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-4756 , L-17581 , NAS 1.15:4756
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
  • 6
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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
  • 7
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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
  • 8
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    Stability characteristics of a conical aerospace plane concept (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Data on stability characteristics of a conical aerospace plane concept were collected for a number of model geometry variations and test conditions, using several NASA-Langley wind tunnels spanning Mach range 0.1-6. The baseline configuration of this plane concept incorporated a 5-deg cone forebody, a 75.96-deg delta wing, a 16-deg leading-edge sweep deployable canard, and a centerline vertical tail. The key results pertinent to stability considerations about all three axes of the model are presented together with data on the effect of the canard on pitch stability, the effect of vertical tail on lateral-directional stability, and the effect of forebody geometry on yaw asymmetries. The experimental stability data are compared with the results from an engineering predictive code.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: SAE PAPER 892313
    Format: text
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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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    High-angle-of-attack stability and control improvements for the EA-6B Prowler (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The factors involved in high-angle-of-attack directional divergence phenomena for the EA-6B ECM aircraft have been investigated in NASA-Langley wind tunnel facilities in order to evaluate airframe modifications which would eliminate or delay such divergence to angles-of-attack farther removed from the operational flight envelope of the aircraft. The results obtained indicate that an adverse sidewash at the aft fuselage and vertical tail location is responsible for the directional stability loss, and that the sidewash is due to a vortex system generated by the fuselage-wing juncture. Modifications encompassing a wing inboard leading edge droop, a wing glove strake, and a vertical fin extension, have significantly alleviated the stability problem.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 87-2361
    Format: text
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    NASA TECHNICAL REPORTS
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