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  • 1
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    A summary of recent large-scale research on high-lift devices (1966)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Wind tunnel model tests of rotating cylinder wing flaps and other high lift devices for STOL AIRCRAFT
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Acoustic characteristics of large-scale STOL models at forward speed (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Wind-tunnel investigations of the acoustic characteristics of the externally blown jet flap (EBF) and augmentor wing STOL concepts are discussed. The large-scale EBF model was equipped with a triple-slotted flap blown by four JT15D turbofan engines with circular, coannular exhaust nozzles. The large-scale augmentor wing model was equipped with an unlined augmentor blown by a slot primary nozzle. The effects of airspeed and angle of attack on the acoustics of the EBF were small. Flap deflection had a greater effect on the acoustics of the augmentor wing than did airspeed. The total sound power was also significantly higher for landing indicating that turning in the augmentor generated acoustic energy. Airspeed produced a small aft shift in acoustic directivity with no significant change in the peak perceived noise levels or sound power levels. Small-scale research of the acoustics for the augmentor wing has shown that by blowing an acoustically treated augmentor with a lobed primary nozzle, the 95-PNdb noise level goal can be achieved or surpassed.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 443-454
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic characteristics of a swept augmentor wing (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: A brief outline of augmentor wing research sponsored by Ames Research Center is presented and is followed by a discussion of large-scale wind-tunnel test results for a swept augmentor wing configuration. The results showed that the augmentor wing could be applied to high-speed swept wing designs with little adverse effect on either the basic performance of the augmentor or the longitudinal characteristics, including maximum lift and stall. Three lateral control devices were shown to be effective and ground effect was measured for several complete aircraft configurations.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 71-86
    Format: text
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  • 4
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    Aspects of investigating STOL noise using large-scale wind-tunnel models. (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The applicability of the NASA Ames 40- by 80-foot wind tunnel for acoustic research on STOL concepts has been investigated. The acoustic characteristics of the wind-tunnel test section have been studied with calibrated acoustic sources. Acoustic characteristics of several large-scale STOL models have been studied in both the free-field and wind-tunnel acoustic environments. The results of these studies indicate that the acoustic characteristics of large-scale STOL models can be measured in the wind tunnel if the test section acoustic environment and model acoustic similitude are taken into consideration. The reverberant field of the test section must be determined with an acoustically similar noise source. A directional microphone, a phased array of microphones, and extrapolation of near-field data to far-field are some of the techniques being explored as possible solutions to the directivity loss in a reverberant field. The model sound pressure levels must be of sufficient magnitude to be distinguishible from the wind-tunnel background noise.
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    V/STOL wind-tunnel testing (1984)
    In:  CASI
    Details
    Publication Date: 2012-05-17
    Description: Factors influencing effective program planning for V/STOL wind-tunnel testing are discussed. The planning sequence itself, which includes a short checklist of considerations that could enhance the value of the tests, is also described. Each of the considerations, choice of wind tunnel, type of model installation, model development and test operations is discussed, and examples of appropriate past and current V/STOL test programs are provided. A short survey of the moderate to large subsonic wind tunnels is followed by a review of several model installations, from dimensional to large-scale models of complete aircraft configurations. Model sizing, power simulation, and planning are treated, including three areas in test operations: data acquisition systems, acoustic measurements in wind tunnels, and flow surveying.
    Keywords: AERODYNAMICS
    Type: AGARD Spec. Course on V(STOL Aerodyn.; 71 p
    Format: text
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  • 6
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    THE EFFECT OF BLADE FLAPPING ON THE DYNAMIC STABILITY OF A TILTING-ROTOR CONVERTIPLANE (1960)
    In:  Other Sources
    Details
    Publication Date: 2013-08-29
    Description: Effect of blade flapping on dynamic stability of tilting-rotor convertiplane - bell xv-3 aircraft
    Keywords: BIOSCIENCES
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Experimental and theoretical studies of wing-leading-edge vortex flow (1966)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Aircraft Aerodynamics; p 297-311
    Format: application/pdf
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  • 8
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    The effect of blade flapping on the dynamic stability of a tilting-rotor convertiplane (1960)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: NASA Conf. on V(STOL Aircraft; p 177-185
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    NASA overview (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The history of NASA efforts at Ames Research Center in researching the performance and application of thrusting augmentors is reviewed. Current objectives include: (1) parametric description of thrust augmentor application to STOL and V/STOL; (2) the use of theoretical and empirical data; (3) aircraft-augmentor integration; and (4) key design considerations for STOL transport and V/STOL fighter aircraft. Test facilities are described and ejector development and performance are assessed.
    Keywords: AERODYNAMICS
    Type: Workshop on Thrust Augmenting Ejectors; p 23-40
    Format: application/pdf
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  • 10
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    Flight investigation of the aerodynamic properties of an Ogee wing (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Flight and wind tunnel tests of low speed characteristics of delta wing aircraft modified to Ogee plan form
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-3071
    Format: application/pdf
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