Boundary layer relaminarization device
AssigneeThe United States of America as represented by the United States National Aeronautics and Space Administration
InventorTheodore R. Creel
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Abstract
Relamination of a boundary layer formed in supersonic flow over the leading edge of a swept airfoil is accomplished using at least one band, especially a quadrangular band, and most preferably a square band. Each band conforms to the leading edge and the upper and lower surfaces of the airfoil as an integral part thereof and extends perpendicularly from the leading edge. Each band has a height of about two times the thickness of the maximum expected boundary layer.
Claims4
A device for relaminarization of a boundary layer formed in supersonic flow over the leading edge of a swept airfoil, the device comprising a square band conforming to the leading edge and the upper and lower surfaces of the swept airfoil as an integral part thereof, the square band being formed in the surface of the airfoil and extending perpendicularly from the leading edge and having a height of about two times the thickness of the maximum expected boundary layer.
A device for relaminarization of a boundary layer formed in supersonic flow over the leading edge of a swept airfoil, the device comprising a band conforming to the leading edge and the upper and lower surfaces of the swept airfoil as an integral part thereof, the band extending perpendicularly from the leading edge and having a height of about two times the thickness of the maximum expected boundary layer, wherein the supersonic flow is Mach 3.5 at a sweep angle of the swept airfoil of 76.degree. over a free-stream Reynolds number of 1.5.times.10.sup.5 to 1.5.times.10.sup.6, and the height of the band is at least 0.01 inches.
Dependencies are inferred from the claim text.