Subsonic and transonic pressure distributions around a bluff afterbody in the wake of a 120⁰ cone for various separation distances /

Calculated mode shapes and pressure distributions at flutter for a highly tapered horizontal tail in subsonic flow /

Hunt, Gerald L.
Walberg, Gerald D.
United States. National Aeronautics and Space Administration.

Cover title."April 1962."Aerodynamics, aircraft; Stresses and loads.Includes bibliographical referen...

Shock-wave shapes and surface pressures on hemisphere- and cone-cylinders in low-density hypersonic flow including ablation /

Monson, Daryl J.
Kuehn, Donald M.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Also available online.Includes bibliographical references (p. 12-13).Also available online.Mode of a...

Flow patterns and pressure distributions around a bluff afterbody in the wake of a 120° cone for various separation distances at Mach 3.0 /

Deveikis, William D.
Sawyer, James Wayne.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

A wind-tunnel investigation of an attached inflatable decelerator concept was conducicd at a Mach nu...

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 ...

Transonic pressure distributions over protuberances and adjacent areas in proximity to the nose of a launch vehicle /

Blackwell, James A.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1966

Cover title."March 1966."Includes bibliographical references (p. 7).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

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

Sphere-cone-cone surface pressure distribution at Mach numbers of 5, 6, 8, and 10 /

Eaton, R. R. author.
Putz, K. E., author.
U.S. Atomic Energy Commission.
Sandia Corporation.

"August 1968."Includes bibliographical references (page 18).Mode of access: Internet

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 on sphere cones /

Ellett, D. M.
Sandia Corporation.

January 1965

"Aerodynamics.""January 1965."Includes bibliographical references.Mode of access: Internet

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

Experimental pressure distributions over blunt two- and three-dimensional bodies having similar cross sections at a mach number of 4.95 /

Julius, Jerome D.
United States. National Aeronautics and Space Administration.

Cover title."September 1959."Flow, mixed; Flow, supersonic; Bodies, thickness distribution.Includes ...

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...

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

Fluctuating surface-pressure characteristics on slender cones in subsonic, supersonic, and hypersonic Mach-number flow /

Heller, H. (Hanno)
Clemente, Anthony R.
Langley Research Center.
Bolt, Beranek, and Newman, inc.

January 1974

"Prepared by Bolt, Beranek, and Newman ... for Langley Research Center."Cover title.Includes bibliog...

Calculated mode shapes and pressure distributions at flutter for a highly tapered horizontal tail in subsonic flow /

Hunt, Gerald L.
Walberg, Gerald D.
United States. National Aeronautics and Space Administration.

Cover title."April 1962."Aerodynamics, aircraft; Stresses and loads.Includes bibliographical referen...

Shock-wave shapes and surface pressures on hemisphere- and cone-cylinders in low-density hypersonic flow including ablation /

Monson, Daryl J.
Kuehn, Donald M.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Also available online.Includes bibliographical references (p. 12-13).Also available online.Mode of a...

Flow patterns and pressure distributions around a bluff afterbody in the wake of a 120° cone for various separation distances at Mach 3.0 /

Deveikis, William D.
Sawyer, James Wayne.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

A wind-tunnel investigation of an attached inflatable decelerator concept was conducicd at a Mach nu...

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 ...

Transonic pressure distributions over protuberances and adjacent areas in proximity to the nose of a launch vehicle /

Blackwell, James A.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1966

Cover title."March 1966."Includes bibliographical references (p. 7).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

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

Sphere-cone-cone surface pressure distribution at Mach numbers of 5, 6, 8, and 10 /

Eaton, R. R. author.
Putz, K. E., author.
U.S. Atomic Energy Commission.
Sandia Corporation.

"August 1968."Includes bibliographical references (page 18).Mode of access: Internet

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 on sphere cones /

Ellett, D. M.
Sandia Corporation.

January 1965

"Aerodynamics.""January 1965."Includes bibliographical references.Mode of access: Internet

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

Experimental pressure distributions over blunt two- and three-dimensional bodies having similar cross sections at a mach number of 4.95 /

Julius, Jerome D.
United States. National Aeronautics and Space Administration.

Cover title."September 1959."Flow, mixed; Flow, supersonic; Bodies, thickness distribution.Includes ...

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...

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

Fluctuating surface-pressure characteristics on slender cones in subsonic, supersonic, and hypersonic Mach-number flow /

Heller, H. (Hanno)
Clemente, Anthony R.
Langley Research Center.
Bolt, Beranek, and Newman, inc.

January 1974

"Prepared by Bolt, Beranek, and Newman ... for Langley Research Center."Cover title.Includes bibliog...

Calculated mode shapes and pressure distributions at flutter for a highly tapered horizontal tail in subsonic flow /

Hunt, Gerald L.
Walberg, Gerald D.
United States. National Aeronautics and Space Administration.

Cover title."April 1962."Aerodynamics, aircraft; Stresses and loads.Includes bibliographical referen...

Shock-wave shapes and surface pressures on hemisphere- and cone-cylinders in low-density hypersonic flow including ablation /

Monson, Daryl J.
Kuehn, Donald M.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Also available online.Includes bibliographical references (p. 12-13).Also available online.Mode of a...

Flow patterns and pressure distributions around a bluff afterbody in the wake of a 120° cone for various separation distances at Mach 3.0 /

Deveikis, William D.
Sawyer, James Wayne.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

A wind-tunnel investigation of an attached inflatable decelerator concept was conducicd at a Mach nu...

Subsonic and transonic pressure distributions around a bluff afterbody in the wake of a 120⁰ cone for various separation distances /

Abstract

Extracted data

Subsonic and transonic pressure distributions around a bluff afterbody in the wake of a 120⁰ cone for various separation distances /

Abstract

Extracted data

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