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Development of Wing InletsLift, drag, internal flow, and pressure distribution measurements were made on a low-drag airfoil incorporating various air inlet designs. Two leading-edge air inlets are developed which feature higher lift coefficients and critical Mach than the basic airfoil. Higher lift coefficients and critical speeds are obtained for leading half of these inlet sections but because of high suction pressures near exist, slightly lower critical speeds are obtained for the entire inlet section than the basic airfoil.
Document ID
19930092761
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Wartime Report
External Source(s)
hdl:2060/19930092761
Authors
Racisz, Stanley F. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 15, 2013
Publication Date
March 1, 1946
Subject Category
Aerodynamics
Report/Patent Number
NACA-ACR-L6B18
NACA-WR-L-727
Accession Number
93R22051
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AIRFOILS - DOUGLAS G-17 - CHAR , MOMENTS & ORDINATES - LOW-DRAG
AIRFOILS - CHARACTERISTICS - EFFECT OF SURFACE ROUGHNESS
PRESSURE DISTRIBUTION - AIRFOILS
WIND TUNNEL TESTS - NACA - LOW-TURBULENCE (7 1/2' X 3')
WING DUCTS
WIND TUNNEL TESTS - NACA - PRESSURE, LOW-TURBULENCE (7 1/2' X-3')
AIR FLOW SYSTEMS, INTERNAL
AIRFOILS - CHAR & MOMENTS - LOW-DRAG (WING FLAPS, SLOTTED-(DOUBLE)
AIRFOILS - CHAR & MOMENTS - LOW-DRAG

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