Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45©� sweptback wing of aspect ratio 4 /

Aerodynamic characteristics of a wing with quarter-chord line swept back 35©�, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section. Transonic-bump method /

Sleeman, William C.
Morrison, William D.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1949

"December 12, 1949."Includes bibliographical references (p. 8).Mode of access: Internet

Transonic investigation of aerodynamic characteristics of a swept-wing fighter-airplane model with leading-edge droop in combination with outboard chord-extensions and notches /

Whitcomb, Charles F.
Norton, Harry T.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, aircraft; Aircraft; Stability and control.Includes bibliographi...

Wind-tunnel investigation of the effects of steady rolling on the aerodynamic loading characteristics of a 45©� sweptback wing at high subsonic speeds /

Wiggins, James W.
Kuhn, Richard E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"November 6, 1953."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Effects of fences, leading-edge chord-extensions, bound-layer ramps, and trailing-edge flaps on the longitudinal stability of a twisted and cambered 60©� sweptback-wing--indented-body configuration at transonic speeds /

Fischetti, Thomas L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

"June 17, 1954."Includes bibliographical references (p. 9).Mode of access: Internet

Aerodynamic loading characteristics in sideslip of a 45©� sweptback wing with and without a fence at high subsonic speeds /

Kuhn, Richard E.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"January 28, 1955."Includes bibliographical references (p. 9).Mode of access: Internet

The effects of an inverse-taper leading-edge flap on the aerodynamic loading characteristics of a 45° sweptback wing at Mach numbers to 0.90 /

Demele, Fred A.
Ames Research Center.

January 1959

"NASA TN D-138.""Ames Research Center, Moffett Field, Calif.""December 1959."Title from cover.Includ...

Spanwise loadings and aerodynamic characteristics for a series of trailing-edge controls on a 40° sweptback wing at Mach numbers of 1.61 and 2.01/

Landrum, Emma Jean.
Czarnecki, K. R.
Langley Research Center.

January 1962

"November 1962."Cover title.Includes bibliographical references (p. 9).Mode of access: Internet

Transonic wind-tunnel investigation of the effects of aspect ratio, spanwise variations in section thickness ratio, and a body indentation on the aerodynamic characteristics of a 45©� sweptback wing-body combination /

Carmel, Melvin M.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

" January 27, 1953."Includes bibliographical references (p. 13).Mode of access: Internet

An investigation of the effects of a geometric twist on the aerodynamic loading characteristics of a 45©� sweptback wing-body configuration at transonic speeds /

Williams, Claude V.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"Declassified September 17, 1958.""October 12, 1954."Cover title.Includes bibliographical references...

Investigation at transonic speeds of aerodynamic characteristics of an unswept semielliptical air inlet in the root of a 45©� sweptback wing /

Bingham, Gene J.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"September 28, 1955."Includes bibliographical references (p. 16).Mode of access: Internet

Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4

Alford, William J , Jr
Spreeman, Kenneth P

February 1954

This investigation was made to determine the effects of 6 degree full-spoan and 3 degree partial-spa...

Aerodynamic characteristics of several cranked leading-edge wing-body combinations at Mach numbers from 0.4 to 2.94 /

Hopkins, Edward J.
Carmichael, Ralph L.
Hicks, Raymond M.
United States. National Aeronautics and Space Administration.
Ames Research Center.

January 1967

"October 1967."Includes bibliographical references (p.21).Mode of access: Internet

Effects of leading-edge bluntness on flutter characteristics of some square-planform double-wedge airfoils at a Mach number of 15.4 /

Goetz, Robert C.
United States. National Aeronautics and Space Administration.

Cover title."October 1962."Aerodynamics, missiles and space vehicles; Stresses and loads.Includes bi...

The effects of wing incidence on the aerodynamic loading characteristics of a sweptback wing-body combination at transonic speeds /

Robinson, Harold L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

"October 12, 1954; Declassified December 1, 1959."Includes bibliographical references (p. 11).Mode o...

A buffet investigation at high subsonic speeds of wing-fuselage-tail combinations having sweptback wings with NACA 64A thickness distributions, fences, a leading-edge extension, and body contouring /

Sutton, Fred B.
Lautenberger, J. Walter, joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

An investigation has been made to determine the effect of wing fences, a wing leading-edge extension...

Aerodynamic characteristics of a wing with quarter-chord line swept back 35©�, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section. Transonic-bump method /

Sleeman, William C.
Morrison, William D.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1949

"December 12, 1949."Includes bibliographical references (p. 8).Mode of access: Internet

Transonic investigation of aerodynamic characteristics of a swept-wing fighter-airplane model with leading-edge droop in combination with outboard chord-extensions and notches /

Whitcomb, Charles F.
Norton, Harry T.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, aircraft; Aircraft; Stability and control.Includes bibliographi...

Wind-tunnel investigation of the effects of steady rolling on the aerodynamic loading characteristics of a 45©� sweptback wing at high subsonic speeds /

Wiggins, James W.
Kuhn, Richard E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"November 6, 1953."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Effects of fences, leading-edge chord-extensions, bound-layer ramps, and trailing-edge flaps on the longitudinal stability of a twisted and cambered 60©� sweptback-wing--indented-body configuration at transonic speeds /

Fischetti, Thomas L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

"June 17, 1954."Includes bibliographical references (p. 9).Mode of access: Internet

Aerodynamic loading characteristics in sideslip of a 45©� sweptback wing with and without a fence at high subsonic speeds /

Kuhn, Richard E.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"January 28, 1955."Includes bibliographical references (p. 9).Mode of access: Internet

The effects of an inverse-taper leading-edge flap on the aerodynamic loading characteristics of a 45° sweptback wing at Mach numbers to 0.90 /

Demele, Fred A.
Ames Research Center.

January 1959

"NASA TN D-138.""Ames Research Center, Moffett Field, Calif.""December 1959."Title from cover.Includ...

Spanwise loadings and aerodynamic characteristics for a series of trailing-edge controls on a 40° sweptback wing at Mach numbers of 1.61 and 2.01/

Landrum, Emma Jean.
Czarnecki, K. R.
Langley Research Center.

January 1962

"November 1962."Cover title.Includes bibliographical references (p. 9).Mode of access: Internet

Transonic wind-tunnel investigation of the effects of aspect ratio, spanwise variations in section thickness ratio, and a body indentation on the aerodynamic characteristics of a 45©� sweptback wing-body combination /

Carmel, Melvin M.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

" January 27, 1953."Includes bibliographical references (p. 13).Mode of access: Internet

An investigation of the effects of a geometric twist on the aerodynamic loading characteristics of a 45©� sweptback wing-body configuration at transonic speeds /

Williams, Claude V.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"Declassified September 17, 1958.""October 12, 1954."Cover title.Includes bibliographical references...

Investigation at transonic speeds of aerodynamic characteristics of an unswept semielliptical air inlet in the root of a 45©� sweptback wing /

Bingham, Gene J.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"September 28, 1955."Includes bibliographical references (p. 16).Mode of access: Internet

Investigation of the Effects of Leading-edge Chord-extensions and Fences in Combination with Leading-edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0.40 to 0.93 of a 45 Degree Sweptback Wing of Aspect Ratio 4

Alford, William J , Jr
Spreeman, Kenneth P

February 1954

This investigation was made to determine the effects of 6 degree full-spoan and 3 degree partial-spa...

Aerodynamic characteristics of several cranked leading-edge wing-body combinations at Mach numbers from 0.4 to 2.94 /

Hopkins, Edward J.
Carmichael, Ralph L.
Hicks, Raymond M.
United States. National Aeronautics and Space Administration.
Ames Research Center.

January 1967

"October 1967."Includes bibliographical references (p.21).Mode of access: Internet

Effects of leading-edge bluntness on flutter characteristics of some square-planform double-wedge airfoils at a Mach number of 15.4 /

Goetz, Robert C.
United States. National Aeronautics and Space Administration.

Cover title."October 1962."Aerodynamics, missiles and space vehicles; Stresses and loads.Includes bi...

The effects of wing incidence on the aerodynamic loading characteristics of a sweptback wing-body combination at transonic speeds /

Robinson, Harold L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

"October 12, 1954; Declassified December 1, 1959."Includes bibliographical references (p. 11).Mode o...

A buffet investigation at high subsonic speeds of wing-fuselage-tail combinations having sweptback wings with NACA 64A thickness distributions, fences, a leading-edge extension, and body contouring /

Sutton, Fred B.
Lautenberger, J. Walter, joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

An investigation has been made to determine the effect of wing fences, a wing leading-edge extension...

Aerodynamic characteristics of a wing with quarter-chord line swept back 35©�, aspect ratio 6, taper ratio 0.6, and NACA 65A006 airfoil section. Transonic-bump method /

Sleeman, William C.
Morrison, William D.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1949

"December 12, 1949."Includes bibliographical references (p. 8).Mode of access: Internet

Transonic investigation of aerodynamic characteristics of a swept-wing fighter-airplane model with leading-edge droop in combination with outboard chord-extensions and notches /

Whitcomb, Charles F.
Norton, Harry T.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, aircraft; Aircraft; Stability and control.Includes bibliographi...

Wind-tunnel investigation of the effects of steady rolling on the aerodynamic loading characteristics of a 45©� sweptback wing at high subsonic speeds /

Wiggins, James W.
Kuhn, Richard E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1954

"November 6, 1953."Cover title.Includes bibliographical references (p. 6).Mode of access: Internet

Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45©� sweptback wing of aspect ratio 4 /

Abstract

Extracted data

Investigation of the effects of leading-edge chord-extensions and fences in combination with leading-edge flaps on the aerodynamic characteristics at Mach numbers of 0.40 to 0.93 of a 45©� sweptback wing of aspect ratio 4 /

Abstract

Extracted data

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