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  • 1
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    Advanced augmentor-wing research (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Results of research on advanced augmentors are discussed. Research concerned with performance has indicated that: (1) augmentors with lobe-type nozzles give higher thrust augmentation than those with slot-type primary nozzles, (2) the thrust of augmentor wings at forward speed is greater than that of internally blown flaps for the speed range of interest, and (3) the optimum augmentor geometry at forward speed may be different from the optimum static geometry. Analysis of augmentor-wing data has shown that the data may be correlated by accounting for the augmentation and entrainment in defining a net thrust coefficient.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 87-96
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Aerodynamic characteristics of a large-scale model with a swept wing and a jet flap having an expandable duct (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The data from an investigation of the aerodynamic characteristics of the expandable duct-jet flap concept are presented. The investigation was made using a large-scale model in the Ames 40- by 80-foot Wind Tunnel. The expandable duct-jet flap concept uses a lower surface, split flap and an upper surface, Fowler flap to form an internal, variable area cavity for the blowing air. Small amounts of blowing are used on the knee of the upper surface flap and the knee of a short-chord, trailing edge control flap. The bulk of the blowing is at the trailing edge. The flap could extend the full span of the model wing or over the inboard part only, with blown ailerons outboard. Primary configurations tested were two flap angles, typical of takeoff and landing; symmetric control flap deflections, primarily for improved landing performance; and asymmetric aileron and control flap deflections, for lateral control.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62281
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic and noise measurements on a quasi-two dimensional augmentor wing model with lobe-type nozzles (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was made of the static, wind-on aerodynamic and static noise characteristics of an augmentor wing having lobe type nozzles. The study was made in the Ames 7-by 10-Foot No. 1 Wind Tunnel using a small-scale, quasi-two-dimensional model. Several configurations of lobe nozzles as well as a normal slot nozzle were tested. Results indicate that lobe nozzles offer improved static and wind-on aerodynamics and reduced static noise relative to slot nozzles. Best wind-on performance was obtained when the tertiary gap was closed even though the static thrust augmentation was maximum with the gap open. Static thrust augmentation, wind-on lift and drag, and static noise directivity are presented as well as typical static and wind-on exit velocity profiles, surface pressure distributions and noise spectrums. The data are presented with limited discussion.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62237
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Advanced augmentor-wing research (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of research on advanced augmentors are discussed. Research concerned with performance indicated that: (1) augmentors with lobe-type nozzles give higher thrust augmentation than those with slot-type primary nozzles; (2) the thrust of augmentor wings at forward speed is greater than that of internally blown flaps for the speed range of interest; and (3) the optimum augmentor geometry at forward speed may be different from the optimum static geometry. Analysis of augmentor-wing data shows that the data may be correlated by accounting for the augmentation and entrainment in defining a net thrust coefficient.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62250
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Results of Full-Scale Wind Tunnel Tests on the H.126 Jet Flap Aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic characteristics of the full-scale H.126 jet flap aircraft were studied in a 40- by 80 foot wind tunnel. The H.126 aircraft is designed for research on flight characteristics of an aircraft using the jet flap principle. Static longitudinal, lateral, and directional characteristics were measured at a Reynolds number of 2.5 to 2.7 million. The jet control power as well as the aerodynamic characteristics were measured and are presented herein with limited discussion. The primary configuration variables were flap and aileron deflection.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7252 , A-3611
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Acoustic characteristics of a large scale wind-tunnel model of a jet flap aircraft (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The expanding-duct jet flap (EJF) concept is studied to determine STOL performance in turbofan-powered aircraft. The EJF is used to solve the problem of ducting the required volume of air into the wing by providing an expanding cavity between the upper and lower surfaces of the flap. The results are presented of an investigation of the acoustic characteristics of the EJF concept on a large-scale aircraft model powered by JT15D engines. The noise of the EJF is generated by acoustic dipoles as shown by the sixth power dependence of the noise on jet velocity. These sources result from the interaction of the flow turbulence with flap of internal and external surfaces and the trailing edges. Increasing the trailing edge jet from 70 percent span to 100 percent span increased the noise 2 db for the equivalent nozzle area. Blowing at the knee of the flap rather than the trailing edge reduced the noise 5 to 10 db by displacing the jet from the trailing edge and providing shielding from high-frequency noise. Deflecting the flap and varying the angle of attack modified the directivity of the underwing noise but did not affect the peak noise. A forward speed of 33.5 m/sec (110 ft/sec) reduced the dipole noise less than 1 db.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3263 , A-5923
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Large-scale V/STOL testing (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Several facets of large-scale testing of V/STOL aircraft configurations are discussed with particular emphasis on test experience in the Ames 40- by 80-Foot Wind Tunnel. Examples of powered-lift test programs are presented in order to illustrate tradeoffs confronting the planner of V/STOL test programs. Large-scale V/STOL wind-tunnel testing can sometimes compete with small-scale testing in the effort required (overall test time) and program costs because of the possibility of conducting a number of different tests with a single large-scale model where several small-scale models would be required. The benefits of both high- or full-scale Reynolds numbers, more detailed configuration simulation, and number and type of onboard measurements are studied.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-73231 , A-7002
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Full-scale wind-tunnel tests of a small unpowered jet aircraft with a T-tail (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to +42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6573 , A-3135
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Large scale wind tunnel investigation of a semispan wing equipped with an externally-blown jet flap (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel investigation was made of the aerodynamic characteristics of a 14.5 foot semispan, externally-blown jet flap model. The model was equipped with a single 30-inch diameter, ducted fan with a 1.03 pressure ratio. The effects of flap size, fan vertical location, and wing sweep on the longitudinal aerodynamic characteristics were studied.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-62079
    Format: application/pdf
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  • 10
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    Evaluation of a new jet flap propulsive-lift system for turbofan-powered STOL transports (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A large-scale STOL transport model with a new jet flap propulsive-lift system was subject to wind-tunnel testing. Aerodynamically, this IBF system combines the benefits of the jet flap and the mechanical flap with boundary layer control. Structurally, it creates its own spanwise air duct with the deflection of the mechanical flap. An additional short-chord control flap, located at the jet-flap exit, provides a powerful means for flight path and lateral controls. The results show that the overall effectiveness of this flap system compares well with other jet flap propulsive-lift systems. A preliminary study based on the wind-tunnel data was made on a medium-size IBF STOL jet transport configuration for a typical-military mission. This study showed that the IBF results in a configuration with a relatively low T/W ratio, making the system an attractive candidate for future designs.
    Keywords: AIRCRAFT
    Type: AIAA PAPER 74-993 , Aircraft Design, Flight Test and Operations Meeting; Aug 12, 1974 - Aug 14, 1974; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
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