초록 ▼

A hybrid laminar flow nacelle for housing an engine of an aircraft includes an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at the leading lip. The nacelle incorporates a suction bleed system between th

A hybrid laminar flow nacelle for housing an engine of an aircraft includes an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at the leading lip. The nacelle incorporates a suction bleed system between the surfaces and a tailored outer surface geometry shape for producing reduced friction drag laminar flow over the outer cowl at cruise operation of the aircraft and producing separation-free flow over the inner surface of the cowl at off-cruise operation of the aircraft.

대표청구항 ▼

A hybrid laminar flow nacelle for housing an engine of an aircraft, comprising: (a) an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at said leading lip; and (b) a suction bleed system including a plural

A hybrid laminar flow nacelle for housing an engine of an aircraft, comprising: (a) an outer annular cowl having a leading lip and radially spaced and axially extending annular outer and inner forward surface portions which merge at said leading lip; and (b) a suction bleed system including a plurality of air suction elements defined in said outer and inner forward surface portions axially downstream from said leading lip in a direction of airflow, suction generating means, and means interconnecting said air suction elements and suction generating means in flow communication; (c) said outer forward surface portion of said cowl having a geometry shape tailored to produce a substantially uniform pressure in a boundary layer airflow along said surface; (d) said suction generating means being operable for applying air suction selectively to said air suction elements to cause bleed of portions of said boundary layer airflow through said air suction elements at said outer surface of said cowl for augmenting reduced friction drag laminar flow over said cowl at cruise operation of the aircraft and to cause bleed of portions of said boundary layer airflow through said air suction elements at said inner surface of said cowl for preventing separation over said inner surface of said cowl at off-cruise operation of the aircraft.