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

Transonic flutter investigation of models of the X-15 airplane horizontal tail /

Young, Lou S.
Bland, Samuel R.
Langley Research Center.

January 1961

"February 1961."Caption title.Includes bibliographical references (p. 14).Mode of access: Internet

Surface pressure data for a supersonic-cruise airplane configuration at mach numbers of 2.30, 2.96, and 3.30 /

Shrout, Barrett L.
Collins, Ida K.
Corlett, William A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

Subject category 02."May 1979"--Cover."Langley Research Center."Includes bibliographical references....

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

McLemore, H. Clyde.
Fink, Marvin P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

"February 17, 1958."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

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

Pressure distribution of a 0.0667-scale model of the X-15 airplane for an angle-of-attack range of 0° to 28° at mach numbers of 2.30, 288, and 4.65 /

Hodge, B. Leon.
Burbank, Paige B.
United States. National Aeronautics and Space Administration.

"May 1960."Cover title.Includes bibliographical references (p. 8).Mode of access: Internet

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...

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

Heat-transfer and pressure measurements on a concove-nose cylinder for a mach number range of 2.49 to 4.44 /

Stallings, Jr., Robert L.
Burbank, Paige B.
Langley Research Center.

January 1959

"October 1959"--Cover.Caption title.Includes bibliographical references (p. 10).Mode of access: Inte...

Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71 /

Morris, W. Douglas.
Couch, Lana M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 12).Mode of access: Internet

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 ...

A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for two trapezoidal and three delta wings having different surface shapes /

Landrum, Emma Jean.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aerodynamics, aircraft; Aircraft;Stresses and loads.Includes bibliograp...

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

Characteristics at mach number of 2.03 of a series of wings having various spanwise distributions of thickness ration and chord /

Robins, A. Warner.
Jackson, Charlie M.
Harris, Roy V.
United States. National Aeronautics and Space Administration.

Cover title."October 1960."Aircraft.Includes bibliographical references.Mode of access: Internet

Measurements of flow properties in the vicinity of three wing-fuselage combinations at Mach numbers of 1.61 and 2.01 /

Carlson, Harry W.
Langley Research Center.

January 1959

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

Wind-tunnel studies at subsonic and transonic speeds of a multiple-mission variable-wing- sweep airplane configuration /

Alford, William J.
Handerson, William P.
Luoma, Arvo A.
Langley Research Center.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 13).Mode of access: Internet

Transonic flutter investigation of models of the X-15 airplane horizontal tail /

Young, Lou S.
Bland, Samuel R.
Langley Research Center.

January 1961

"February 1961."Caption title.Includes bibliographical references (p. 14).Mode of access: Internet

Surface pressure data for a supersonic-cruise airplane configuration at mach numbers of 2.30, 2.96, and 3.30 /

Shrout, Barrett L.
Collins, Ida K.
Corlett, William A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

Subject category 02."May 1979"--Cover."Langley Research Center."Includes bibliographical references....

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

McLemore, H. Clyde.
Fink, Marvin P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

"February 17, 1958."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

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

Pressure distribution of a 0.0667-scale model of the X-15 airplane for an angle-of-attack range of 0° to 28° at mach numbers of 2.30, 288, and 4.65 /

Hodge, B. Leon.
Burbank, Paige B.
United States. National Aeronautics and Space Administration.

"May 1960."Cover title.Includes bibliographical references (p. 8).Mode of access: Internet

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...

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

Heat-transfer and pressure measurements on a concove-nose cylinder for a mach number range of 2.49 to 4.44 /

Stallings, Jr., Robert L.
Burbank, Paige B.
Langley Research Center.

January 1959

"October 1959"--Cover.Caption title.Includes bibliographical references (p. 10).Mode of access: Inte...

Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71 /

Morris, W. Douglas.
Couch, Lana M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 12).Mode of access: Internet

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 ...

A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for two trapezoidal and three delta wings having different surface shapes /

Landrum, Emma Jean.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aerodynamics, aircraft; Aircraft;Stresses and loads.Includes bibliograp...

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

Characteristics at mach number of 2.03 of a series of wings having various spanwise distributions of thickness ration and chord /

Robins, A. Warner.
Jackson, Charlie M.
Harris, Roy V.
United States. National Aeronautics and Space Administration.

Cover title."October 1960."Aircraft.Includes bibliographical references.Mode of access: Internet

Measurements of flow properties in the vicinity of three wing-fuselage combinations at Mach numbers of 1.61 and 2.01 /

Carlson, Harry W.
Langley Research Center.

January 1959

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

Wind-tunnel studies at subsonic and transonic speeds of a multiple-mission variable-wing- sweep airplane configuration /

Alford, William J.
Handerson, William P.
Luoma, Arvo A.
Langley Research Center.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 13).Mode of access: Internet

Transonic flutter investigation of models of the X-15 airplane horizontal tail /

Young, Lou S.
Bland, Samuel R.
Langley Research Center.

January 1961

"February 1961."Caption title.Includes bibliographical references (p. 14).Mode of access: Internet

Surface pressure data for a supersonic-cruise airplane configuration at mach numbers of 2.30, 2.96, and 3.30 /

Shrout, Barrett L.
Collins, Ida K.
Corlett, William A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

Subject category 02."May 1979"--Cover."Langley Research Center."Includes bibliographical references....

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

McLemore, H. Clyde.
Fink, Marvin P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

"February 17, 1958."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

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

Abstract

Extracted data

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

Abstract

Extracted data

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