Method for stabilizing laminar separated boundary layers

Details Method for stabilizing laminar separated boundary layers Method for stabilizing laminar separated boundary layers

1986-08-15

1987-05-12

Peters, Jr., Joseph F.

Aeronautics and astronautics

Aircraft sustentation

Sustaining airfoils

244199, 244208, 244130, B64C 2106, B64C 2108

Patent

active

046643451

ABSTRACT:
Separated laminar flow boundary layers are stabilized by delaying a transition into a turbulent flow and by reducing the size of the laminar boundary layer separation zone downstream of a disturbance in the surface contour of a body in the flow, such as a backward step in the body surface, e.g., where sheet metal layers overlap in the surface of an aircraft wing. This purpose is accomplished by suction inlets in the surface just upstream of the disturbance and blowing outlets just downstream of the disturbance and by a flow channel interconnecting these inlets and outlets. Passage of a portion of the flowing medium through these passages is automatically assured due to a pressure differential between the inlets and outlets.

REFERENCES:
patent: 3128063 (1964-04-01), Kaplan
patent: 3261576 (1966-07-01), Valyi
patent: 3360221 (1967-12-01), Heskestad
patent: 3507463 (1970-04-01), Kuntz
patent: 3820628 (1974-06-01), Hanson
"Laminar Flow a Reality", May 15, 1982, Flight.
Hahn & Pfenninger, J. Aircraft, 10 (1973) pp. 618-622, "Prevention of Tration over Backward Step by Suction".
Truckenbrodt-Schlichting, "Aerodynamik des Flugzeugs", vol. 1, 1959, Publ.: Springer Verlag, pp. 260 to 263.

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