HYBRID LAMINAR FLOW NACELLE

13DV-8904 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 surf ace . portions which merge at the leading lip. The nacelle incorporates a suction bleed syst...

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Bibliographic Details
Main Authors LAHTI, DANIEL J, MUNGUR, PERMANAD, YATES, DAVID E, STOCKMAN, NORBERT O
Format Patent
LanguageEnglish
French
Published 01.12.1990
Edition5
Subjects
AEROPLANES
AIR INTAKES FOR JET-PROPULSION PLANTS
AIRCRAFT
ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT
AVIATION
BLASTING
COMBUSTION ENGINES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
COSMONAUTICS
ENGINE PLANTS IN GENERAL
EQUIPMENT FOR FITTING IN OR TO AIRCRAFT
FLYING SUITS
GAS-TURBINE PLANTS
HEATING
HELICOPTERS
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
PARACHUTES
PERFORMING OPERATIONS
STEAM ENGINES
TRANSPORTING
WEAPONS
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Summary:13DV-8904 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 surf ace . 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 surf ace of the cowl at off-cruise operation of the aircraft.
Bibliography:Application Number: CA19902012248