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  • 1
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    Aerodynamic and performance characteristics of externally blown flap configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The application of externally blown flaps for improving the performance of short takeoff aircraft is discussed. The characteristics of externally blown flap powered lift are examined. A method for predicting the aerodynamic performance of a particular externally blown flap configuration is presented. The following specific effects are analyzed: (1) induced aerodynamics, (2) static turning, (3) flap span and deflection, and (4) engine size and chord flap.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 43-54
    Format: text
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  • 2
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    Interaction of grid turbulence with a uniform mean shear (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Grid turbulence interaction with uniform mean shear flow, examining initial disturbance length scale effects
    Keywords: AERODYNAMICS
    Type: ; YAL SOCIETY (
    Format: text
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  • 3
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    Low speed wind tunnel flow field results for JT8D refan engines on the Boeing 727-200 (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Low speed flow angularity results are presented showing flow direction at the nacelle locations on the Boeing 727-200. Flow angle probes (yawheads) were used for measurements at side and center inlet positions on the aft fuselage. A range of flap settings were tested with flap angles of 0 deg, 15 deg, and 40 deg selected for investigation.
    Keywords: AERODYNAMICS
    Type: NASA-CR-134630 , D6-43098
    Format: application/pdf
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  • 4
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    Inverse problem approach to the design of short two-dimensional diffusers. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: AERODYNAMICS
    Type: ASME PAPER 72-WA/GT-6 , Winter Annual Meeting of the American Society of Mechanical Engineers; Nov 26, 1972 - Nov 30, 1972; New York, NY
    Format: text
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  • 5
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    An experimental investigation of base heating on typical Mars entry body shapes. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Hypersonic experiments on wire supported high angle blunt cones were conducted to determine the base heating characteristics. Heating distributions were obtained for several base configurations with variations in free stream Reynolds Number and gas composition. The dependence of the heating in the base region on angle of attack was also investigated. It was found that gas composition effects can be accounted for by comparison at equal Reynolds Number. Angle of attack effects can result in either increasing or decreasing base heating depending upon the location in the base region.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 72-317 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; Apr 10, 1972 - Apr 12, 1972; San Antonio, TX
    Format: text
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  • 6
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    A wind tunnel investigation of the wake near the trailing edge of a deflected externally blown flap (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The model tested was a general research model of a swept-wing, jet-powered STOL transport with externally blown flaps. The model was tested with four engine simulators mounted on pylons under the wing. Tests were conducted in the V/STOL tunnel over an angle of attack range of 0 deg to 16 deg and a thrust coefficient range from 0 to approximately 4 at a Reynolds number of 0.461 x 1 million based on the wing reference chord. The results of this investigation are presented primarily as plots of the individual velocity vectors obtained from the wake survey. These data are used to extend an earlier analysis to isolate the effects of the engine thrust on the behavior of the flow at the flap trailing edge. Results of a comparison with a jet-flap theory are also shown.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3079 , L-9665
    Format: application/pdf
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  • 7
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    The design and performance of axially symmetrical contoured wall diffusers employing suction boundary layer control (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a procedure for the design and the performance prediction of axially symmetrical contoured wall diffusers employing suction boundary layer control. An inverse problem approach was used in the potential flow design of the diffuser wall contours. The experimentally observed flow characteristics and the stability of flows within the diffuser are also described. Guidelines for the design of low suction (less than 10 percent of the inlet flow) and thus high effectiveness contoured wall diffusers are also provided based on the results of the experimental program.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 74-GT-152 , Gas Turbine Conference and Products Show; Mar 30, 1974 - Apr 04, 1974; Zurich; Switzerland
    Format: text
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  • 8
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    Effect of limited amplitude and rate of flap motion on vane-controlled gust alleviation system (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An airplane (light transport type) is assumed to be in level flight (no pitching) through atmospheric turbulence which has a mean-square vertical gust intensity of 9.3 (m/sec)sq. The power spectral density of the vertical acceleration due to gusts is examined with and without a gust-alleviation system in operation. The gust-alleviation system consisted of wing flaps that were used in conjunction with a vane mounted ahead of the airplane to sense the vertical gust velocity. The primary purpose of this study was to examine the change in the effectiveness of the gust-alleviation system when the flap motion is limited in amplitude and rate. The alleviation system was very effective if no restrictions were placed on flap motion (rate and amplitude). Restricting the flap amplitude to 0.5 radian did not appreciably change the effectiveness. However, restricting the flap rate did reduce the gust alleviation, and restricting the flap rate to 0.25 rad/sec actually caused the alleviation system to increase the vertical acceleration above that for the no-alleviation situation. Based upon this analysis, rate limiting appears to be rather significant in gust-alleviation systems designed for passenger comfort.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6733 , L-8027
    Format: application/pdf
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  • 9
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    Effect of several porous casing treatments on stall limit and on overall performance of an axial flow compressor rotor (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Several geometrically different porous casings were tested with an axial-flow compressor rotor to determine their effects upon the rotor stall-limit line and overall performance. The tests were conducted using both uniform and nonuniform inlet-flow conditions. The rotor performance with the various casing treatments is compared with that obtained with a solid casing. The ability of the various casing treatments to displace the rotor stall-limit line to lower weight flows was observed. Significant stall-margin increases were obtained with several of the porous casings. Peak efficiencies with two of the porous casings were as high as or slightly higher than that obtained with solid casing.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-6537 , E-5973
    Format: application/pdf
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  • 10
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    Slowly oscillating lifting surfaces at subsonic and supersonic speeds. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The paper presents an unsteady aerodynamic influence coefficient method based on the low-frequency approximation. The influence coefficients are of a type which have been used to compute steady flow about wing-body combinations; therefore, the new method may be extended readily to low-frequency unsteady flow about wing-body combinations. The validity of the method is demonstrated by comparisons with numerical results from conventional, unsteady lifting surface methods. The method is valid for arbitrary wings in supersonic flow and for wings of finite span in subsonic flow. The method, when extended to include wing-body-tail interactions, will have important applications for predicting stability, control, and gust response characteristics of large airplanes. Dynamic stability derivatives and pressure distributions are given for several planforms. The comparison with either analytical or other well established numerical methods shows good agreement.-
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 9; Nov. 197
    Format: text
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