Surface pressure distributions on a large-scale 49©� sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge /

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...

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).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

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

Local pressure distribution on a blunt delta wing for angles of attack up to 35 degrees at Mach numbers of 3.4 and 4.7

Kussoy, Marvin.
United States. National Aeronautics and Space Administration.

Cover title."December 1962."Includes bibliographical references.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...

Pressure measurements on a hypersonic glide configuration having 79.5° sweepback and 45° dihedral at a Mach number of 4.95 /

Cooper, Morton.
Gunn, Charles R.
Langley Research Center.

January 1959

"November 1959"--Cover.Caption title.Includes bibliographical references (p. 8).Mode of access: Inte...

Approximate solutions for the flow about flat-top wing-body configurations at high supersonic airspeeds /

Savin, Raymond C.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

On front cover: "September 15, 1958."Includes bibliographical references: p. 35-36.Mode of access: I...

Pressure measurements obtained in flight at transonic speeds for a conically cambered delta wing /

Keener, Earl R.
Flight Research Center (U.S.)

January 1959

"October 1959."Cover title.Includes bibliographical references (p. 14-15).Mode of access: Internet

Effect of longitudinal wings position on the pressure characteristics at transonic speeds of a 45©� sweptback wing-fuselage model /

Solomon, William.
Schmeer, James W.
United States. National Advisory Committee for Aeronautics.

"March 4, 1953."Cover title.Includes bibliographical references (p. 12).Mode of access: Internet

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

Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 /

Cubbison, Robert W.
Ward, James J.
Anderson, Bernhard H.
Lewis Research Center.

Prepared at Lewis Research Center."February 1961."Cover title.Includes bibliographical references (p...

Pressure measurements of the leading edge of a swept wing at Mach 2.2 /

Sorrells, Russell B.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 11).Mode of ...

Subsonic aerodynamic characteristics of an airplane configuration utilizing a variable-sweep wing having a free-floating apex /

Polhamus, Edward C., 1948-
Hammond, Alexander D.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1965

"July 1965"--Cover.Cover title.Includes bibliographical references (p. 9).Mode of access: Internet

Tabulated data from a pressure-distribution investigation at mach number 2.01 of the wing of a canard airplane model /

Driver, Cornelius.
Jacocks, James L.
Langley Research Center.

January 1959

"December 1959"--Cover.Caption title.Includes bibliographical references (p. 5).Mode of access: Inte...

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...

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).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

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

Local pressure distribution on a blunt delta wing for angles of attack up to 35 degrees at Mach numbers of 3.4 and 4.7

Kussoy, Marvin.
United States. National Aeronautics and Space Administration.

Cover title."December 1962."Includes bibliographical references.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...

Pressure measurements on a hypersonic glide configuration having 79.5° sweepback and 45° dihedral at a Mach number of 4.95 /

Cooper, Morton.
Gunn, Charles R.
Langley Research Center.

January 1959

"November 1959"--Cover.Caption title.Includes bibliographical references (p. 8).Mode of access: Inte...

Approximate solutions for the flow about flat-top wing-body configurations at high supersonic airspeeds /

Savin, Raymond C.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

On front cover: "September 15, 1958."Includes bibliographical references: p. 35-36.Mode of access: I...

Pressure measurements obtained in flight at transonic speeds for a conically cambered delta wing /

Keener, Earl R.
Flight Research Center (U.S.)

January 1959

"October 1959."Cover title.Includes bibliographical references (p. 14-15).Mode of access: Internet

Effect of longitudinal wings position on the pressure characteristics at transonic speeds of a 45©� sweptback wing-fuselage model /

Solomon, William.
Schmeer, James W.
United States. National Advisory Committee for Aeronautics.

"March 4, 1953."Cover title.Includes bibliographical references (p. 12).Mode of access: Internet

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

Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 /

Cubbison, Robert W.
Ward, James J.
Anderson, Bernhard H.
Lewis Research Center.

Prepared at Lewis Research Center."February 1961."Cover title.Includes bibliographical references (p...

Pressure measurements of the leading edge of a swept wing at Mach 2.2 /

Sorrells, Russell B.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 11).Mode of ...

Subsonic aerodynamic characteristics of an airplane configuration utilizing a variable-sweep wing having a free-floating apex /

Polhamus, Edward C., 1948-
Hammond, Alexander D.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1965

"July 1965"--Cover.Cover title.Includes bibliographical references (p. 9).Mode of access: Internet

Tabulated data from a pressure-distribution investigation at mach number 2.01 of the wing of a canard airplane model /

Driver, Cornelius.
Jacocks, James L.
Langley Research Center.

January 1959

"December 1959"--Cover.Caption title.Includes bibliographical references (p. 5).Mode of access: Inte...

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...

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).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

Surface pressure distributions on a large-scale 49©� sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge /

Abstract

Extracted data

Surface pressure distributions on a large-scale 49©� sweptback wing-body-tail configuration with blowing applied over the flaps and wing leading edge /

Abstract

Extracted data

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