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  • 1
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    Wind Tunnel Aerodynamic Characteristics of a Transport-type Airfoil in a Simulated Heavy Rain Environment (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of simulated heavy rain on the aerodynamic characteristics of an NACA 64-210 airfoil section equipped with leading-and trailing-edge high-lift devices were investigated in the Langley 14- by 22-Foot Subsonic Tunnel. The model had a chord of 2.5 ft, a span of 8 ft, and was mounted on the tunnel centerline between two large endplates. Aerodynamic measurements in and out of the simulated rain environment were obtained for dynamic pressures of 30 and 50 psf and an angle-of-attack range of 0 to 20 degrees for the cruise configuration. The rain intensity was varied to produce liquid water contents ranging from 16 to 46 gm/cu m. The results obtained for various rain intensity levels and tunnel speeds showed significant losses in maximum lift capability and increases in drag for a given lift as the liquid water content was increased. The results obtained on the landing configuration also indicate a progressive decrease in the angle of attack at which maximum lift occurred and an increase in the slope of the pitching-moment curve as the liquid water content was increased. The sensitivity of test results to the effects of the water surface tension was also investigated. A chemical was introduced into the rain environment that reduced the surface tension of water by a factor of 2. The reduction in the surface tension of water did not significantly alter the level of performance losses for the landing configuration.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3184 , L-16959 , NAS 1.60:3184
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Operational considerations for aerodynamic testing of large-scale wing sections in a simulated natural rain environment (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: One of the necessary areas of consideration for outdoor heavy rain testing is the effect of wind on both the simulated rain field and the quality and repeatability of the aerodynamic data. This paper discusses the data acquisition and subsequent reduction to nondimensional coefficients of lift and drag, with the appropriate correction for wind and rain field. Sample force data showing these effects are presented, along with estimates for accuracy and repeatability. The capability to produce high-quality data for rain drop size distribution using photographic and computerized image processing techniques was developed. Sample photographs depicting rain drop size are shown.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0485
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The development of a facility for full-scale testing of airfoil performance in simulated rain (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: NASA Langley's Aircraft Landing Dynamics Facility has been adapted in order to test the performance of airfoils in a simulated rain environment, at rainfall rates of 2, 10, 30, and 40 inches/hour, and thereby derive the scaling laws associated with simulated rain in wind tunnel testing. A full-scale prototype of the rain-generation system has been constructed and tested for suitable rain intensity, uniformity, effects of crosswinds on uniformity, and drop size range. The results of a wind tunnel test aimed at ascertaining the minimum length of the simulated rain field required to yield an airfoil performance change due to the rain environment are presented.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 88-0055
    Format: text
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  • 4
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    Wind tunnel test results of heavy rain effects on airfoil performance (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effects of simulated heavy rain on the aerodynamic characteristics of a NACA 64-210 airfoil section equipped with high-lift devices were investigated in the NASA Langley 14- by 22-Foot Subsonic Tunnel. The experiment was part of an on-going NASA program to determine the effect of heavy rain on airplane performance, and was directed at providing insight into scaling laws for subscale model testing of rain effects. The model used in the investigation had a chord of 2.5 feet, a span of 8.0 feet, and was mounted on the tunnel centerline between two large endplates. A water spray distribution system was located 10 chord lengths upstream of the model. The sensitivity of test results to partial-span coverage of the model in the simulated rain environment as compared to full-span coverage was also investigated. The lift and drag data obtained for the high-lift configuration show excellent repeatability of results compared to the previous data. Results obtained for various spray concentrations and tunnel speeds showed significant losses in maximum lift capability, a decrease in the angle of attack for maximum lift, and an increase in drag as the stimulated rain rate was increased. The test results also indicated that the data were not strongly affected by surface tension effects for the high-lift configuration.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-0260
    Format: text
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  • 5
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    Results of aerodynamic testing of large-scale wing sections in a simulated natural rain environment (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The NASA Langley Research Center has developed a large-scale ground testing capability for evaluating the effect of heavy rain on airfoil lift. The paper presents the results obtained at the Langley Aircraft Landing Dynamics Facility on a 10-foot cord NACA 64-210 wing section equipped with a leading-edge slat and double-slotted trailing-edge flap deflected to simulate landing conditions. Aerodynamic lift data were obtained with and without the rain simulation system turned on for an angle-of-attack range of 7.5 to 19.5 deg and for two rainfall conditions: 9 in/hr and 40 in/hr. The results are compared to and correlated with previous small-scale wind tunnel results for the same airfoil section. It appears that to first order, scale effects are not large and the wind tunnel research technique can be used to predict rain effects on airplane performance.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0486
    Format: text
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