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  • 1
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    Compressible flow in a diffusing S-duct with flow separation (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Local flow velocity vectors, as well as static and total pressures along ten radial traverses, were obtained at six stations for secondary flows in a diffusing 30-30-deg S-duct with circular cross section. The strong secondary flow measured in the first bend continued into the second with new vorticity produced in the opposite direction. Contour plots representing the transverse velocity field, as well as total and static pressure contours, have been obtained. As a result of the secondary flow and subsequent separation, substantial total pressure distortion is noted to occur at the duct exit.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Measurements of compressible secondary flow in a circular S-duct (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of an experimental study of secondary flow in a circular cross section 30 deg - 30 deg S-duct with entrance Mach number of 0.6. Local flow velocity vectors have been measured along the length of the duct at six stations. These measurements have been made using a five-port cone probe. Static and total pressure profiles in the transverse planes are obtained from the cone probe measurements. Wall static pressure measurements along three azimuth angles of 0 deg, 90 deg, and 180 deg along the duct are also made. Contour plots presenting the three dimensional velocity field as well as the total- and static-pressure fields are obtained. Surface oil flow visualization technique has been used to provide details of the flow on the S-duct boundaries. The experimental observations have been compared with typical computational results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1739
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Flow control in a diffusing S-Duct (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Accurate measurements have been made of secondary flow in a 1.51 area ratio diffusing 30 deg - 30 deg S-Duct with circulair cross section. Turbulent flow was entering the duct at Mach number of 0.6, the boundary layer thickness at the duct entrance was ten percent of the duct inlet diameter. Through measurements made, local flow velocity vector as well as static and total pressures mapping of the flow at several stations were obtained. Strong secondary flow was measured in the first bend which continued into the second bend with new vorticity produced in there in the opposite direction. Surface oil flow visualization and wall pressures indicated a region of separated flow starting at theta approximately equal to 22 deg on the inside of the first bend up to theta approximately equal to 44 deg on the outside of the second bend. The flow separated in 'cyclone' form and never reattached in the duct. As a result of the secondary flow and the flow separation, significant total pressure distortion was observed at the exit of the duct. Using flow control devices the separation was eliminated while the exit distortion was improved.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0524
    Format: text
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    NASA TECHNICAL REPORTS
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