Flowfield Measurements Inside a Boundary-Layer Bleed Slot

Davis, D. O.; Willis, B. P.; Hingst, W. R.

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.

Document ID

19970022219

Acquisition Source

Legacy CDMS

Document Type

Reprint (Version printed in journal)

Authors

Date Acquired

September 6, 2013

Publication Date

October 1, 1996

Publication Information

Publication: AIAA Journal

Publisher: American Institute of Aeronautics and Astronautics

Volume: 34

Issue: 10

Subject Category

Report/Patent Number

Meeting Information

Meeting: Aerospace Sciences

Location: Reno, NV

Country: United States

Start Date: January 9, 1995

End Date: January 12, 1995

Sponsors: American Inst. of Aeronautics and Astronautics

Accession Number

97N22798

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Public

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