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  • 1985-1989  (6)
  • 1
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    Exploratory evaluation of moving-model technique for measurement of dynamic ground effects (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Journal of Aircraft (ISSN 0021-8669); 25; 557-562
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    An assessment of ground effects determined by static and dynamic testing techniques (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A new testing technique was developed wherein the rate of descent can be included as a parameter in ground effects investigations. This technique simulates the rate of descent by horizontal motion of a model over an inclined ground board in the Langley Vortex Research Facility (VRF) During initial evaluations of the technique, dynamic ground effects data were obtained over the inclined ground board, steady state ground effects data were obtained over a flat portion of the ground board, and the results were compared to conventional static wind tunnel ground effect data both with and without a moving belt ground plane simulation. Initial testing and analysis led to the following conclusions: the moving belt ground plane had little effect on static ground effects for the configurations tested unless thrust reversers were employed; in general, rate-of-descent reduced ground effects to the point that for reversed thrust cases an expected loss of lift due to ground effects was eliminated at approach conditions; and, in general, the steady state results from the VRF matched static results obtained from the wind tunnel once the flow field stabilized over the flat portion of the ground board.
    Keywords: AERODYNAMICS
    Type: NASA, Ames Research Center, The 1987 Ground Vortex Workshop; p 121-146
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of a moving-model technique for measuring ground effect (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A ground-based testing technique is under development for the measurement of dynamic or time-dependent ground effects which may be present during aircraft approach and landing. The technique utilizes a model moving horizontally over an upwardly-inclined ground plane to simulate rate of descent. Results were obtained in the Langley Research Center (LaRC) Vortex Research Facility (VRF) for a generic 60 delta wing and for an F-18 configuration, both with and without thrust reversing, at forward speeds up to 100 ft/sec. These same models and support hardware were also tested in the LaRC 14 by 22 Foot Subsonic Tunnel at identical conditions (but without rate of descent) with and without a moving-belt ground plane to obtain data for comparison.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4080 , L-16481 , NAS 1.15:4080
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Exploratory evaluation of a moving-model technique for measurement of dynamic ground effects (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An attempt is presently made to measure the dynamic or time-dependent ground effects that may be encountered by aircraft during approach and landing by means of a ground-based testing technique that employs a model moving horizontally over an upwardly inclined ground plane to simulate the rate of descent. Results have been thus obtained for a 60-deg delta wing and for an F-18 full configuration, with and without thrust reversal, at forward speeds of up to 100 ft/sec. An analysis of the results gathered indicates that ground effects were reduced when the rate of descent was included in the test conditions.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 87-1924
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    A review of technologies applicable to low-speed flight of high-performance aircraft investigated in the Langley 14- x 22-foot subsonic tunnel (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An extensive research program has been underway at the NASA Langley Research Center to define and develop the technologies required for low-speed flight of high-performance aircraft. This 10-year program has placed emphasis on both short takeoff and landing (STOL) and short takeoff and vertical landing (STOVL) operations rather than on regular up and away flight. A series of NASA in-house as well as joint projects have studied various technologies including high lift, vectored thrust, thrust-induced lift, reversed thrust, an alternate method of providing trim and control, and ground effects. These technologies have been investigated on a number of configurations ranging from industry designs for advanced fighter aircraft to generic wing-canard research models. Test conditions have ranged from hover (or static) through transition to wing-borne flight at angles of attack from -5 to 40 deg at representative thrust coefficients.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2796 , L-16364 , NAS 1.60:2796
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A comparison of the ground effects measured with and without rate-of-descent modeling on the F-15 S/MTD configuration (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The effect of descent rate (DR) on the approach aerodynamics of the F-15 S/MTD aircraft is investigated experimentally using a moving model in the NASA Langley Vortex Research Facility. A 0.083-scale low-speed rotary-balance model equipped with a thrust-reverser simulator and with grit strips to assure turbulent flow was tested in an approach configuration at forward speed 60 ft/sec, corresponding to DR = 4.19 ft/sec. The results are presented in extensive graphs and compared with wind-tunnel data on the same configuration at DR = 0. Significant differences are attributed to the DR in the present experiments and the presence of a ground boundary layer in the wind-tunnel tests. It is predicted that safe approaches could be made with the lower thrust reverser vectored up to 80 deg, or even 110 deg if the DR were not arrested near the ground.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 89-3280 , AIAA Flight Simulation Technologies Conference and Exhibit; Aug 14, 1989 - Aug 16, 1989; Boston, MA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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