An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and a 40©� sweepback : pressure distribution measurements of the interference effect of the wing on the fuselage at Mach numbers of 1.40 and 1.59 /

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

Investigation at transonic speeds of the loading over a 40 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2 and NACA 65A004 airfoil sections /

Runckel, Jack F.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, aircraft; Aircraft; Stresses and loads.Includes bibliographical...

Investigation of pitch maneuver speed margins for a supersonic transport configuration with a variable-sweep wing /

Sawyer, Richard H.
Silsby, Norman S.
McLaughlin, Milton D.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1967

"October 1967."Includes bibliographical references (p. 15).Mode of access: Internet

Preliminary results of the flight investigation between Mach numbers of 0.80 and 1.36 of a rocket-powered model of a supersonic airplane configuration having a tapered wing with circular-arc sections and 40©� sweepback /

D'Aiutolo, Charles T.
Mason, Homer P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"October 31, 1950. Declassified September 17, 1958."Cover title.Includes bibliographical references ...

A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel /

Hasel, Lowell E.
Sinclair, Archibald R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.

January 1950

"April 7, 1950; Declassified May 29, 1959."Includes bibliographical references (p. 14).Mode of acces...

Transonic wind-tunnel investigation of the interference between a 45©� sweptback wing and a systematic series of four bodies /

Loving, Donald L.
Wornom, Dewey E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"November 20, 1952; Declassified October 18, 1956."Includes bibliographical references (p. 14).Mode ...

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch at M = 2.0 /

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

January 1952

"July 28, 1952."Includes bibliographical references (p. 7-8).Mode of access: Internet

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

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 1.60 of nacelle shape and position on the aerodynamic characteristics in pitch of two wing-body combinations with a 47©� sweptback wings /

Hasel, Lowell E.
Sevier, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"Januayr 12, 1952."Includes bibliographical references (p. 7).Mode of access: Internet

Preliminary results of supersonic-jet tests of simplified wing structures /

Heldenfels, Richard R.
Rosecrans, Richard.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"July 8, 1953."Includes bibliographical references (p. 15).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

An experimental transonic investigation of a 45©� sweptback wing-body combination with several types of body indentation with theoretical comparisons included /

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

January 1954

"November 19,1954."Includes bibliographical references (p. 11).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

Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds. Aspect-ratio series /

Fournier, Paul G.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"February 9, 1953."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

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

Investigation at transonic speeds of the loading over a 40 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2 and NACA 65A004 airfoil sections /

Runckel, Jack F.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, aircraft; Aircraft; Stresses and loads.Includes bibliographical...

Investigation of pitch maneuver speed margins for a supersonic transport configuration with a variable-sweep wing /

Sawyer, Richard H.
Silsby, Norman S.
McLaughlin, Milton D.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1967

"October 1967."Includes bibliographical references (p. 15).Mode of access: Internet

Preliminary results of the flight investigation between Mach numbers of 0.80 and 1.36 of a rocket-powered model of a supersonic airplane configuration having a tapered wing with circular-arc sections and 40©� sweepback /

D'Aiutolo, Charles T.
Mason, Homer P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"October 31, 1950. Declassified September 17, 1958."Cover title.Includes bibliographical references ...

A pressure-distribution investigation of a supersonic-aircraft fuselage and calibration of the Mach number 1.40 nozzle of the Langley 4- by 4-foot supersonic tunnel /

Hasel, Lowell E.
Sinclair, Archibald R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics.

January 1950

"April 7, 1950; Declassified May 29, 1959."Includes bibliographical references (p. 14).Mode of acces...

Transonic wind-tunnel investigation of the interference between a 45©� sweptback wing and a systematic series of four bodies /

Loving, Donald L.
Wornom, Dewey E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"November 20, 1952; Declassified October 18, 1956."Includes bibliographical references (p. 14).Mode ...

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effects of sweep angle and thickness ratio on the aerodynamic characteristics in pitch at M = 2.0 /

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

January 1952

"July 28, 1952."Includes bibliographical references (p. 7-8).Mode of access: Internet

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

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2 : effect at M = 1.60 of nacelle shape and position on the aerodynamic characteristics in pitch of two wing-body combinations with a 47©� sweptback wings /

Hasel, Lowell E.
Sevier, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"Januayr 12, 1952."Includes bibliographical references (p. 7).Mode of access: Internet

Preliminary results of supersonic-jet tests of simplified wing structures /

Heldenfels, Richard R.
Rosecrans, Richard.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"July 8, 1953."Includes bibliographical references (p. 15).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

An experimental transonic investigation of a 45©� sweptback wing-body combination with several types of body indentation with theoretical comparisons included /

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

January 1954

"November 19,1954."Includes bibliographical references (p. 11).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

Wind-tunnel investigation of the static lateral stability characteristics of wing-fuselage combinations at high supersonic speeds. Aspect-ratio series /

Fournier, Paul G.
Byrnes, Andrew L.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"February 9, 1953."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

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

Investigation at transonic speeds of the loading over a 40 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2 and NACA 65A004 airfoil sections /

Runckel, Jack F.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, aircraft; Aircraft; Stresses and loads.Includes bibliographical...

Investigation of pitch maneuver speed margins for a supersonic transport configuration with a variable-sweep wing /

Sawyer, Richard H.
Silsby, Norman S.
McLaughlin, Milton D.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1967

"October 1967."Includes bibliographical references (p. 15).Mode of access: Internet

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and a 40©� sweepback : pressure distribution measurements of the interference effect of the wing on the fuselage at Mach numbers of 1.40 and 1.59 /

Abstract

Extracted data

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and a 40©� sweepback : pressure distribution measurements of the interference effect of the wing on the fuselage at Mach numbers of 1.40 and 1.59 /

Abstract

Extracted data

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