Comparisons of theoretical and experimental pressure distributions over a wing-body model at high supersonic speeds /

Aerodynamic testing technique for twin-fuselage models at hypersonic speeds /

Ashby, George C.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 6).Mode of a...

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 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...

Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds /

Jernell, Lloyd S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10).Mode of ...

Pressure distributions for a rectangular supersonic inlet at subsonic speeds /

Fuller, Dennis E.
Langley Research Center.

January 1976

Research prepared at Langley Research Center.Cover title.Bibliography: p. 9.Mode of access: Internet

Fuselage and nozzle pressure distributions on a 1/12-scale F-15 propulsion model at transonic speeds /

Pendergraft, Odis C.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1979

"November 1979"--Cover."Langley Research Center."Includes bibliographical references.Mode of access:...

Experimental cavity pressure distributions at supersonic speeds /

Stallings, Robert L.
Wilcox, Floyd J. (Floyd Jay)
Langley Research Center.

January 1987

Prepared at Langley Research Center."June 1987"--Cover.Includes bibliographical references (p. 9).Mo...

Measured pressure distributions on large-angle cones in hypersonic flows of tetrafluoromethane, air, and helium /

Jones, Robert A.
Hunt, James L. (James Larry), 1939-
Langley Research Center.

January 1973

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode ...

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 ...

Pressure distributions induced by elevon deflections on swept wings and adjacent end-plate surfaces at Mach 6 /

Kaufman, Louis G., II.
Johnson, Charles B.
Langley Research Center.
United States. National Aeronautics and Space Administration.

Prepared by Langley Research Center, Hampton, VA 23665.Includes bibliographical references (p. 13-1...

Experimental pressure distributions for a family of blunt bodies at Mach numbers from 2.49 to 4.63 and angles of attack from 0 ̊to 15 /

Stallings, Robert L.
Howell, Dorothy T.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1969

Pressure distributions for blunt body wind tunnel models at supersonic speeds and angles of attack f...

Basic pressure measurements on a 0.0667-scale model of the North American X-15 research airplane at transonic speeds /

Osborne, Robert S.
Stafford, Virginia C.
Langley Research Center.
United States. National Aeronautics and Space Administration.

"Langley Research Center, Langely Field, Va.""October 1960."Cover title.Includes bibliographical ref...

Flight measurements of surface pressures on a flexible supercritical research wing /

Eckstrom, Clinton V.
Langley Research Center.

January 1985

Prepared at Langley Research Center."December 1985"--Cover.Includes bibliographical references (p. 1...

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

Numerical methods for the design and analysis of wings at supersonic speeds /

Carlson, Harry W.
Miller, David S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 29-30).Mode ...

Aerodynamic testing technique for twin-fuselage models at hypersonic speeds /

Ashby, George C.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 6).Mode of a...

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 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...

Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds /

Jernell, Lloyd S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10).Mode of ...

Pressure distributions for a rectangular supersonic inlet at subsonic speeds /

Fuller, Dennis E.
Langley Research Center.

January 1976

Research prepared at Langley Research Center.Cover title.Bibliography: p. 9.Mode of access: Internet

Fuselage and nozzle pressure distributions on a 1/12-scale F-15 propulsion model at transonic speeds /

Pendergraft, Odis C.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1979

"November 1979"--Cover."Langley Research Center."Includes bibliographical references.Mode of access:...

Experimental cavity pressure distributions at supersonic speeds /

Stallings, Robert L.
Wilcox, Floyd J. (Floyd Jay)
Langley Research Center.

January 1987

Prepared at Langley Research Center."June 1987"--Cover.Includes bibliographical references (p. 9).Mo...

Measured pressure distributions on large-angle cones in hypersonic flows of tetrafluoromethane, air, and helium /

Jones, Robert A.
Hunt, James L. (James Larry), 1939-
Langley Research Center.

January 1973

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode ...

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 ...

Pressure distributions induced by elevon deflections on swept wings and adjacent end-plate surfaces at Mach 6 /

Kaufman, Louis G., II.
Johnson, Charles B.
Langley Research Center.
United States. National Aeronautics and Space Administration.

Prepared by Langley Research Center, Hampton, VA 23665.Includes bibliographical references (p. 13-1...

Experimental pressure distributions for a family of blunt bodies at Mach numbers from 2.49 to 4.63 and angles of attack from 0 ̊to 15 /

Stallings, Robert L.
Howell, Dorothy T.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1969

Pressure distributions for blunt body wind tunnel models at supersonic speeds and angles of attack f...

Basic pressure measurements on a 0.0667-scale model of the North American X-15 research airplane at transonic speeds /

Osborne, Robert S.
Stafford, Virginia C.
Langley Research Center.
United States. National Aeronautics and Space Administration.

"Langley Research Center, Langely Field, Va.""October 1960."Cover title.Includes bibliographical ref...

Flight measurements of surface pressures on a flexible supercritical research wing /

Eckstrom, Clinton V.
Langley Research Center.

January 1985

Prepared at Langley Research Center."December 1985"--Cover.Includes bibliographical references (p. 1...

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

Numerical methods for the design and analysis of wings at supersonic speeds /

Carlson, Harry W.
Miller, David S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 29-30).Mode ...

Aerodynamic testing technique for twin-fuselage models at hypersonic speeds /

Ashby, George C.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 6).Mode of a...

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 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...

Comparisons of theoretical and experimental pressure distributions over a wing-body model at high supersonic speeds /

Abstract

Extracted data

Comparisons of theoretical and experimental pressure distributions over a wing-body model at high supersonic speeds /

Abstract

Extracted data

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