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

Aeordynamic characteristics of a distinct wing-body configuration at Mach 6 : experiment, theory, and the hypersonic isolation principle /

Penland, Jim A.
Pittman, Jimmy L.
Langley Research Center.

January 1985

Prepared at Langley Research Center."August 1985"--Cover.Includes bibliographical references (p. 10)...

Effects of flow separation and cove leakage on pressure and heat-transfer distributions along a wing-cove-elevon configuration at Mach 6.9 /

Deveikis, William D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1983

"June 1983"--Cover.Distributed to depository libraries in microfiche.Includes bibliographical refere...

Detailed pressure distribution measurements obtained on several configurations of an aspect-ratio-7 variable twist wing /

Holbrook, G. Thomas.
Dunham, Dana Morris.
Langley Research Center.

January 1985

Prepared at Langley Research Center."March 1985."Includes bibliographical references (p. 4).Mode of ...

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 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

Pressure and heat-transfer distributions in a simulated wing-elevon cove with variable leakage at a free-stream Mach number of 6.9 /

Deveikis, William D.
Bartlett, Whitney.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1978

Dec. 1978."Langley Research Center, Hampton, Virginia."Includes bibliographical references.Mode of a...

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

Kaufman, L. G., II
Johnson, C. B.

April 1977

Surface pressure distributions are presented for regions where three-dimensional separated flow effe...

Pressure distributions and shock shapes for 12.84/̊7 ̊on-axis and bent-nose biconics in air at mach 6 /

Miller, Charles G. (Charles George), 1940-
Gnoffo, Peter A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject category 02."December 1981"--Cover."Langley Research Center."Mode of access: Internet

Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 /

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

January 1960

"NASA TN D-236.""Langley Research Center, Langley Field, Va.""April 1960."Cover title.Includes bibli...

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

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

Jernell, Lloyd S.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1971

Prepared at Langley Research Center.N71-35197.Cover title.Includes bibliographical references (p. 8)...

Methods for estimating pressure and thermal loads induced by elevon deflections on hypersonic-vehicle surfaces with turbulent boundary layers /

Kàufman, Louis G.
Johnson, Charles B.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject Category 34."September 1981"--Cover."Langley Research Center."Includes bibliographical refer...

Heat-transfer and pressure measurements on a simulated elevon deflected 30 ̊near flight conditions at Mach 7 /

Johnson, Charles B.
Weinstein, Irving, joint author.
Taylor, Allan H., joint author.
United States. National Aeronautics and Space Administration.

January 1977

Issued Sept. 1977.Includes bibliographical references (p. 12).Mode of access: Internet

Aerodynamic pressures and heating rates on surfaces between split elevons at Mach 6.6 /

Hunt, L. Roane (Lewis Roane)
United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.

January 1988

"December 1988"--Cover.Includes bibliographical references (p. 13).Mode of access: Internet

Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 /

Miller, David S.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

"April 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: In...

Aeordynamic characteristics of a distinct wing-body configuration at Mach 6 : experiment, theory, and the hypersonic isolation principle /

Penland, Jim A.
Pittman, Jimmy L.
Langley Research Center.

January 1985

Prepared at Langley Research Center."August 1985"--Cover.Includes bibliographical references (p. 10)...

Effects of flow separation and cove leakage on pressure and heat-transfer distributions along a wing-cove-elevon configuration at Mach 6.9 /

Deveikis, William D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1983

"June 1983"--Cover.Distributed to depository libraries in microfiche.Includes bibliographical refere...

Detailed pressure distribution measurements obtained on several configurations of an aspect-ratio-7 variable twist wing /

Holbrook, G. Thomas.
Dunham, Dana Morris.
Langley Research Center.

January 1985

Prepared at Langley Research Center."March 1985."Includes bibliographical references (p. 4).Mode of ...

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 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

Pressure and heat-transfer distributions in a simulated wing-elevon cove with variable leakage at a free-stream Mach number of 6.9 /

Deveikis, William D.
Bartlett, Whitney.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1978

Dec. 1978."Langley Research Center, Hampton, Virginia."Includes bibliographical references.Mode of a...

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

Kaufman, L. G., II
Johnson, C. B.

April 1977

Surface pressure distributions are presented for regions where three-dimensional separated flow effe...

Pressure distributions and shock shapes for 12.84/̊7 ̊on-axis and bent-nose biconics in air at mach 6 /

Miller, Charles G. (Charles George), 1940-
Gnoffo, Peter A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject category 02."December 1981"--Cover."Langley Research Center."Mode of access: Internet

Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 /

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

January 1960

"NASA TN D-236.""Langley Research Center, Langley Field, Va.""April 1960."Cover title.Includes bibli...

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

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

Jernell, Lloyd S.
United States. National Aeronautics and Space Administration.
Langley Research Center.

January 1971

Prepared at Langley Research Center.N71-35197.Cover title.Includes bibliographical references (p. 8)...

Methods for estimating pressure and thermal loads induced by elevon deflections on hypersonic-vehicle surfaces with turbulent boundary layers /

Kàufman, Louis G.
Johnson, Charles B.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject Category 34."September 1981"--Cover."Langley Research Center."Includes bibliographical refer...

Heat-transfer and pressure measurements on a simulated elevon deflected 30 ̊near flight conditions at Mach 7 /

Johnson, Charles B.
Weinstein, Irving, joint author.
Taylor, Allan H., joint author.
United States. National Aeronautics and Space Administration.

January 1977

Issued Sept. 1977.Includes bibliographical references (p. 12).Mode of access: Internet

Aerodynamic pressures and heating rates on surfaces between split elevons at Mach 6.6 /

Hunt, L. Roane (Lewis Roane)
United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.

January 1988

"December 1988"--Cover.Includes bibliographical references (p. 13).Mode of access: Internet

Pressure and force data for a flat wing and a warped conical wing having a shockless recompression at Mach 1.62 /

Miller, David S.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

"April 1981"--Cover."Langley Research Center."Includes bibliographical references.Mode of access: In...

Aeordynamic characteristics of a distinct wing-body configuration at Mach 6 : experiment, theory, and the hypersonic isolation principle /

Penland, Jim A.
Pittman, Jimmy L.
Langley Research Center.

January 1985

Prepared at Langley Research Center."August 1985"--Cover.Includes bibliographical references (p. 10)...

Effects of flow separation and cove leakage on pressure and heat-transfer distributions along a wing-cove-elevon configuration at Mach 6.9 /

Deveikis, William D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1983

"June 1983"--Cover.Distributed to depository libraries in microfiche.Includes bibliographical refere...

Detailed pressure distribution measurements obtained on several configurations of an aspect-ratio-7 variable twist wing /

Holbrook, G. Thomas.
Dunham, Dana Morris.
Langley Research Center.

January 1985

Prepared at Langley Research Center."March 1985."Includes bibliographical references (p. 4).Mode of ...

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

Abstract

Extracted data

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

Abstract

Extracted data

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