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  • 1
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    Flow Coefficient Behavior for Boundary Layer Bleed Holes and Slots (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation into the flow coefficient behavior for nine boundary layer bleed orifice configurations is reported. This test was conducted for the purposes of exploring boundary layer control through mass flow removal and does not address issues of stability bleed. Parametric data consist of bleed region flow coefficient as a function of Mach number, bleed plenum pressure, and bleed orifice geometry. Seven multiple hole configurations and two single slot configurations were tested over a supersonic Mach number range of 1.3 to 2.5 (nominal). Advantages gained by using multiple holes in a bleed region instead of a single spanwise slot are discussed and the issue of modeling an entire array of bleed orifices based on the performance of a single orifice is addressed. Preconditioning the flow approaching a 90 degree inclined (normal) hole configuration resulted in a significant improvement in the performance of the configuration. The same preconditioning caused only subtle changes in performance for a 20 degree inclined (slanted) configuration.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-106846 , E-9420 , NAS 1.15:106846 , AIAA PAPER 95-0031 , Aerospace Sciences Meeting and Exhibit; Jan 09, 1995 - Jan 12, 1995; Reno, NV; United States
    Format: application/pdf
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  • 2
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    Porous and Microporous Honeycomb Composites as Potential Boundary-Layer Bleed Materials (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results of an experimental investigation are presented in which the use of porous and microporous honeycomb composite materials is evaluated as an alternate to perforated solid plates for boundary-layer bleed in supersonic aircraft inlets. The terms "porous" and "microporous," respectively, refer to bleed orifice diameters roughly equal to and much less than the displacement thickness of the approach boundary-layer. A Baseline porous solid plate, two porous honeycomb, and three microporous honeycomb configurations are evaluated. The performance of the plates is characterized by the flow coefficient and relative change in boundary-layer profile parameters across the bleed region. The tests were conducted at Mach numbers of 1.27 and 1.98. The results show the porous honeycomb is not as efficient at removing mass compared to the baseline. The microporous plates were about equal to the baseline with one plate demonstrating a significantly higher efficiency. The microporous plates produced significantly fuller boundary-layer profiles downstream of the bleed region for a given mass flow removal rate than either the baseline or the porous honeycomb plates.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TM-113160 , NAS 1.15:113160 , AIAA Paper 97-3260 , E-10911 , Joint Propulsion Conference and Exhibit; Jul 06, 1997 - Jul 09, 1997; Seattle, WA; United States
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    NASA TECHNICAL REPORTS
  • 3
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    Flowfield Measurements in a Slot-Bled Oblique Shock Wave and Turbulent Boundary-Layer Interaction (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation was conducted to determine the flowfield inside a bleed slot used to control an oblique shock-wave and turbulent boundary-layer interaction. The slot was oriented normal to the primary flow direction and had a width of 1.0 cm (primary flow direction), a length of 2.54 cm, and spanned 16.5 cm. The approach boundary layer upstream of the interaction was nominally 3.0 cm thick. Two operating conditions were studied: M = 1.98 with a shock generator deflection angle of 6 deg and M= 2.46 with a shock generator deflection angle of 8 deg. Measurements include surface and flowfield static pressure, Pitot pressure, and total mass-flow through the slot. The results show that despite an initially two-dimensional interaction for the zero bleed-flow case, the slot does not remove mass uniformly in the spanwise direction. Inside the slot, the flow is characterized by two separation regions which significantly reduce the effective flow area. The upper separation region acts as an aerodynamic throat resulting in supersonic flow through much of the slot.
    Keywords: Aerodynamics
    Type: NASA/TM-1998-206974 , E-11126 , NAS 1.15:206974 , AIAA Paper 95-0032 , Aerospace Sciences Meeting and Exhibit; Jan 09, 1995 - Jan 12, 1995; Reno, NV; United States
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  • 4
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    Flowfield Measurements Inside a Boundary-Layer Bleed Slot (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation was conducted to determine the flowfield inside a bleed slot used to control an oblique shock-wave and turbulent boundary-layer interaction. The slot was oriented normal to the primary flow direction and had a width of 1.0 cm (primary flow direction) and a length of 2.54 cm and spanned 16.5 cm. The approach boundary layer upstream of the interaction was nominally 3.0 cm thick. Two operating conditions were studied: M = 1.98 with a shock generator deflection angle of 6 deg and M = 2.46 with a shock generator deflection angle of 8 deg. Measurements include surface and flowfield static pressure, pitot pressure, and total mass flow through the slot. The results show that despite an initially two-dimensional interaction for the zero-bleed-flow case, the slot does not remove mass uniformly in the spanwise direction. Inside the slot, the flow is characterized bv two separation regions, which significantly reduce the effective flow area. The upper separation region acts as an aerodynamic throat, resulting in supersonic flow through much of the slot.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TM-112763 , NAS 1.15:112763 , AIAA Paper 95-0032 , AIAA Journal; 34; 10; 1977-1983|Aerospace Sciences; Jan 09, 1995 - Jan 12, 1995; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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