Pressure measurements for Mach five flows over a blunt pyramidal configuration with aerodynamic controls : part of an investigation of hypersonic flow separation and control characteristics /

An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 /

Holloway, Paul F.
Creekmore, Helen S.
Sterrett, James R.
Langley Research Center.

Prepared at Langley Research Center."November 1965"--Cover.Includes bibliographical references (p. 3...

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

Base pressure measurements on sharp and blunt 9©� cones at Mach numbers from 3.50 to 9.20 /

Zarin, Neil A. (Neil Arthur), 1938-
U.S. Army Ballistic Research Laboratory.
U.S. Atomic Energy Commission.

"RDT&E Project No. 1A222901A201.""November 1965."Includes bibliographical references (page 35).Mode ...

Pressure measurements for mach five flows over winged re-entry configurations with aerodynamic controls.

Kaufman, Louis G., II., author.
Air Force Flight Dynamics Laboratory (U.S.). sponsor.
Wright-Patterson Air Force Base. Flight Dynamics Laboratory. Research and Technology Division. issuing body.
Grumman Aircraft Engineering Corporation. sponsor.

Includes bibliograpical references (page 4).Air Force Contract No.Mode of access: Internet

Pressure and heat transfer measurements for Mach 8 flows over a blunt pryamidal configuration with aerodynamic controls.

Kaufman, Louis G., II., author.
United States. Air Force. Systems Command. issuing body.
Air Force Flight Dynamics Laboratory (U.S.). sponsor.
Grumman Aircraft Engineering Corporation. Research Department. sponsor.

Includes bibliograpical references (pages 7-8 ).Air Force Contract No.Mode of access: Internet

Pressure measurements on sharp and blunt 5 degreee and 15 degree-half-angle cones at mach number 3.86 and angles of attack to 100 degrees /

Amick, James L.
United States. National Aeronautics and Space Administration.

Cover title."February 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibl...

Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock.

Scheuing, Richard A., author.
Melnik, Robert E., author.
Brook, John W., author.
Mead, Harold R., author.
Aeronautical Research Associates of Princeton. sponsor.
Grumman Aircraft Engineering Corporation. sponsor.
United States. Air Force. Systems Command. Aeronautical Systems Division. issuing body.
United States. Air Force. Systems Command. Aeronautical Systems Division. Directorate of Materials and Processesd States. sponsor.
United States. Aerospace Medical Division. sponsor.

"May 1962."Includes bibliographical references (pages 174-177).Flight Control Laboratory Contract No...

Flow phenomena in starting a hypersonic shock tunnel /

Glick, Herbert S., author.
Smith, William E., 1925-. author.
Hertzberg, Abraham., author.
United States. Air Force. Air Research and Development Command. sponsor.
Arnold Engineering Development Center. sponsor.
Cornell Aeronautical Laboratory. issuing body.

"March 1955."Includes bibliographical references (pages 24-25).Print reproduction.U.S. Air Force Con...

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 ...

Pressure data for four analytically defined arrow wings in supersonic flow /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Sept. 1980."Langley Research Center."Bibliography: p. 16.Mode of access: Internet

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 ...

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...

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 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

Preliminary base pressures obtained from the X-15 airplane at mach numbers from 1.1 to 3.2 /

Saltzman, Edwin J.
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Aerodynamics, aircraft;Aerodynamics, missiles and space vehicles; Vehicle ...

An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 /

Holloway, Paul F.
Creekmore, Helen S.
Sterrett, James R.
Langley Research Center.

Prepared at Langley Research Center."November 1965"--Cover.Includes bibliographical references (p. 3...

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

Base pressure measurements on sharp and blunt 9©� cones at Mach numbers from 3.50 to 9.20 /

Zarin, Neil A. (Neil Arthur), 1938-
U.S. Army Ballistic Research Laboratory.
U.S. Atomic Energy Commission.

"RDT&E Project No. 1A222901A201.""November 1965."Includes bibliographical references (page 35).Mode ...

Pressure measurements for mach five flows over winged re-entry configurations with aerodynamic controls.

Kaufman, Louis G., II., author.
Air Force Flight Dynamics Laboratory (U.S.). sponsor.
Wright-Patterson Air Force Base. Flight Dynamics Laboratory. Research and Technology Division. issuing body.
Grumman Aircraft Engineering Corporation. sponsor.

Includes bibliograpical references (page 4).Air Force Contract No.Mode of access: Internet

Pressure and heat transfer measurements for Mach 8 flows over a blunt pryamidal configuration with aerodynamic controls.

Kaufman, Louis G., II., author.
United States. Air Force. Systems Command. issuing body.
Air Force Flight Dynamics Laboratory (U.S.). sponsor.
Grumman Aircraft Engineering Corporation. Research Department. sponsor.

Includes bibliograpical references (pages 7-8 ).Air Force Contract No.Mode of access: Internet

Pressure measurements on sharp and blunt 5 degreee and 15 degree-half-angle cones at mach number 3.86 and angles of attack to 100 degrees /

Amick, James L.
United States. National Aeronautics and Space Administration.

Cover title."February 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibl...

Theoretical prediction of pressures in hypersonic flow with special reference to configurations having attached leading-edge shock.

Scheuing, Richard A., author.
Melnik, Robert E., author.
Brook, John W., author.
Mead, Harold R., author.
Aeronautical Research Associates of Princeton. sponsor.
Grumman Aircraft Engineering Corporation. sponsor.
United States. Air Force. Systems Command. Aeronautical Systems Division. issuing body.
United States. Air Force. Systems Command. Aeronautical Systems Division. Directorate of Materials and Processesd States. sponsor.
United States. Aerospace Medical Division. sponsor.

"May 1962."Includes bibliographical references (pages 174-177).Flight Control Laboratory Contract No...

Flow phenomena in starting a hypersonic shock tunnel /

Glick, Herbert S., author.
Smith, William E., 1925-. author.
Hertzberg, Abraham., author.
United States. Air Force. Air Research and Development Command. sponsor.
Arnold Engineering Development Center. sponsor.
Cornell Aeronautical Laboratory. issuing body.

"March 1955."Includes bibliographical references (pages 24-25).Print reproduction.U.S. Air Force Con...

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 ...

Pressure data for four analytically defined arrow wings in supersonic flow /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Sept. 1980."Langley Research Center."Bibliography: p. 16.Mode of access: Internet

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 ...

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...

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 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

Preliminary base pressures obtained from the X-15 airplane at mach numbers from 1.1 to 3.2 /

Saltzman, Edwin J.
United States. National Aeronautics and Space Administration.

Cover title."August 1961."Aerodynamics, aircraft;Aerodynamics, missiles and space vehicles; Vehicle ...

An investigation of heat transfer within regions of separated flow at a Mach number of 6.0 /

Holloway, Paul F.
Creekmore, Helen S.
Sterrett, James R.
Langley Research Center.

Prepared at Langley Research Center."November 1965"--Cover.Includes bibliographical references (p. 3...

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

Zarin, Neil A. (Neil Arthur), 1938-
U.S. Army Ballistic Research Laboratory.
U.S. Atomic Energy Commission.

"RDT&E Project No. 1A222901A201.""November 1965."Includes bibliographical references (page 35).Mode ...

Pressure measurements for Mach five flows over a blunt pyramidal configuration with aerodynamic controls : part of an investigation of hypersonic flow separation and control characteristics /

Abstract

Extracted data

Pressure measurements for Mach five flows over a blunt pyramidal configuration with aerodynamic controls : part of an investigation of hypersonic flow separation and control characteristics /

Abstract

Extracted data

Related items

Related items