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naca-tn-728

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National Advisory Committee for Aeronautics, Technical Notes - Wind Tunnel Investigation of an NACA 23021 Airfoil with Two Arrangements of a 40% Chord Slotted Flap

naca-tn-728-wind-tunnel-investigation-of-an-naca-23021-airfoil-with-two-arrangements-of-a-40-chord-slotted-flap-1

An investigation was made in the N.A.C.A. 7— by lOn
foot wind tunnel of an N.A.C.A. 23021 airfoil with two
arrangements of e 4O~3ercent~chord slotted flap. The ef—
fect of slot shape, flap Position, and flap deflection on
the section aerodynamic characteristics was determined."
The envelope polars and the section aerodynamic characteré
istics are given and are compared with those-of an N.A.C.A.
23021 airfoil with a 35.66—percent-chord slotted flap and
of an N.A.C.A. 23012 airfoil with a 40—percent-chord slot-
ted flap. -Eletted contours of flag-nose positions for ,
maximum lift and nininun drug were used ior selecting op-
timum flap paths.

Both the maximum lift coefficients and the minimum
drag coefficients were higher for the E.A.G.A.’23021 air-
foil with the 40-percentvchord flap than for the HaA.G.A.
33021 airfoil with the 25.66-perecnt—chord flap. but the
percentage increase in drag Was greater than the perdentage
increase in lift. A connarison of the aerodynamic charac—
teristics of the H.A.C.A. 23021 airfoil with a 40-percent-
chord-flap and of the H.A.C.A. 23012 airfoil with a 40-
percent—chord flap Showed that the thick Section reached
approximately the same maximum lift as the thin section but,
as anticipated, had a considerably higher drag coefficient.

The National Advisory Committee for Aeronautics is con-
ducting an extensive investigation to determine the rela—
tive merits of various types of lift—increasing devices. H
For use in take—off, a highelift device capable of produc-
ing.high lift with low drag is desirable. For use in land—
ings, however. high-lift with variable drag is believed
desirable. The slotted flaps being investi- rated by the
N. A. C. A. are apparently capable_ of fulfilling these con-
flicting require-meats.

The purpose of the present_tests was to determine
the aerodynamic characteristics of the K.A.C.A. 23021 air-
foil with a 40—percent—chord slotted flap. The section
aerodynamic characteristics of the present airfoil—flap
combination are compared with those of an H.A.C.A. 23021
airfoil with a 25.66—fierccnt—chord slotted flap and of an
N.A.C.A. 23012 airfoil with a 40—percent—chord slotted
flap.

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naca-tn-728

  • Version
  • 155 Downloads
  • 896.86 KB File Size
  • 1 File Count
  • November 30, 2016 Create Date
  • November 30, 2016 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Technical Notes - Wind Tunnel Investigation of an NACA 23021 Airfoil with Two Arrangements of a 40% Chord Slotted Flap

naca-tn-728-wind-tunnel-investigation-of-an-naca-23021-airfoil-with-two-arrangements-of-a-40-chord-slotted-flap-1

An investigation was made in the N.A.C.A. 7— by lOn
foot wind tunnel of an N.A.C.A. 23021 airfoil with two
arrangements of e 4O~3ercent~chord slotted flap. The ef—
fect of slot shape, flap Position, and flap deflection on
the section aerodynamic characteristics was determined."
The envelope polars and the section aerodynamic characteré
istics are given and are compared with those-of an N.A.C.A.
23021 airfoil with a 35.66—percent-chord slotted flap and
of an N.A.C.A. 23012 airfoil with a 40—percent-chord slot-
ted flap. -Eletted contours of flag-nose positions for ,
maximum lift and nininun drug were used ior selecting op-
timum flap paths.

Both the maximum lift coefficients and the minimum
drag coefficients were higher for the E.A.G.A.’23021 air-
foil with the 40-percentvchord flap than for the HaA.G.A.
33021 airfoil with the 25.66-perecnt—chord flap. but the
percentage increase in drag Was greater than the perdentage
increase in lift. A connarison of the aerodynamic charac—
teristics of the H.A.C.A. 23021 airfoil with a 40-percent-
chord-flap and of the H.A.C.A. 23012 airfoil with a 40-
percent—chord flap Showed that the thick Section reached
approximately the same maximum lift as the thin section but,
as anticipated, had a considerably higher drag coefficient.

The National Advisory Committee for Aeronautics is con-
ducting an extensive investigation to determine the rela—
tive merits of various types of lift—increasing devices. H
For use in take—off, a highelift device capable of produc-
ing.high lift with low drag is desirable. For use in land—
ings, however. high-lift with variable drag is believed
desirable. The slotted flaps being investi- rated by the
N. A. C. A. are apparently capable_ of fulfilling these con-
flicting require-meats.

The purpose of the present_tests was to determine
the aerodynamic characteristics of the K.A.C.A. 23021 air-
foil with a 40—percent—chord slotted flap. The section
aerodynamic characteristics of the present airfoil—flap
combination are compared with those of an H.A.C.A. 23021
airfoil with a 25.66—fierccnt—chord slotted flap and of an
N.A.C.A. 23012 airfoil with a 40—percent—chord slotted
flap.

FileAction
naca-tn-728 Wind Tunnel Investigation of an NACA 23021 Airfoil with Two Arrangements of a 40% Chord Slotted Flap.pdfDownload 
17,005 Documents in our Technical Library
2449357 Total Downloads

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Newest Additions

NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
AA-CP-20212-001
AA-CP-20212-001
ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...