Measurements of aerodynamic heat transfer in turbulent separated regions at a Mach number of 1.8 /

Preliminary results from a free-flight investigation of boundary-layer transition and heat transfer on a highly polished 8-inch-diameter hemisphere-cylinder at Mach numbers up to 3 and Reynolds numbers based on a length of 1 foot up to 17.7 x 10⁶ /

Hall, James R.
Piland, Robert O.
Speegle, Katherine C.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"May 16, 1957."Includes bibliographical references (p. 11).Mode of access: Internet

Local afterbody heat transfer to a blunt two-dimensional configuration at Mach 8 /

Bushnell, Dennis M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."July 1968Includes bibliographical references (p. 21-22).Mode of access: Internet

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

Heat-transfer measurements at a Mach number of 2 in the turbulent boundary layer on a flat plate having a stepwise temperature distribution /

Conti, Raul J. (Raul Jorge)
Langley Research Center.

Prepared at Langley Research Center."November 1959."Cover title.Includes bibliographical references ...

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...

Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29©� /

Rumsey, Charles B.
Lee, Dorothy B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"January 24, 1958; Declassified February 8, 1963."Includes bibliographical references (p. 17).Mode o...

Aerodynamic heating and heat transfer phenomena at Mach numbers 3 to 4 /

Anderson, K. G., author.
Durben, J. M., author.
Merrell, H. B., author.
Wright Air Development Center. issuing body.
United States. Air Force. Air Research and Development Command. sponsor.

"December 1951."Includes bibliographical references (pages 45-47).Aero Medical Laboratory Contract N...

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

Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 /

Rumsey, Charles B. (Charles Bertrand)
Hopko, Russell N.
Piland, Robert Owens.
Langley Research Center.

Prepared at Langley Research Center."January 1960."Cover title.Includes bibliographical references (...

Measurements of aerodynamic heating obtained during demonstration flight tests of the Douglas D-558-II airplane /

Jones, Ira P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"November 26, 1952."Includes bibliographical references (p. 8).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...

Measurements of aerodynamic heat transfer and boundary-layer transition on a 10 degree cone in free flight at supersonic mach numbers up to 5.9 /

Rumsey, Charles B.
Lee, Dorothy B.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics; Vehicle performan...

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

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 measurements and comparison with flight of the boundary layer and heat transfer on a hollow cylinder at Mach 3 /

Stallings, Robert L.
Lamb, Milton.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Dec. 1980."Langley Research Center."Includes bibliographical references.Mode of access: Internet

Preliminary results from a free-flight investigation of boundary-layer transition and heat transfer on a highly polished 8-inch-diameter hemisphere-cylinder at Mach numbers up to 3 and Reynolds numbers based on a length of 1 foot up to 17.7 x 10⁶ /

Hall, James R.
Piland, Robert O.
Speegle, Katherine C.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"May 16, 1957."Includes bibliographical references (p. 11).Mode of access: Internet

Local afterbody heat transfer to a blunt two-dimensional configuration at Mach 8 /

Bushnell, Dennis M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."July 1968Includes bibliographical references (p. 21-22).Mode of access: Internet

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

Heat-transfer measurements at a Mach number of 2 in the turbulent boundary layer on a flat plate having a stepwise temperature distribution /

Conti, Raul J. (Raul Jorge)
Langley Research Center.

Prepared at Langley Research Center."November 1959."Cover title.Includes bibliographical references ...

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...

Heat-transfer measurements in free flight at Mach numbers up to 14.6 on a flat-faced conical nose with a total angle of 29©� /

Rumsey, Charles B.
Lee, Dorothy B.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"January 24, 1958; Declassified February 8, 1963."Includes bibliographical references (p. 17).Mode o...

Aerodynamic heating and heat transfer phenomena at Mach numbers 3 to 4 /

Anderson, K. G., author.
Durben, J. M., author.
Merrell, H. B., author.
Wright Air Development Center. issuing body.
United States. Air Force. Air Research and Development Command. sponsor.

"December 1951."Includes bibliographical references (pages 45-47).Aero Medical Laboratory Contract N...

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

Aerodynamic-heating data obtained from free-flight tests between Mach numbers of 1 and 5 /

Rumsey, Charles B. (Charles Bertrand)
Hopko, Russell N.
Piland, Robert Owens.
Langley Research Center.

Prepared at Langley Research Center."January 1960."Cover title.Includes bibliographical references (...

Measurements of aerodynamic heating obtained during demonstration flight tests of the Douglas D-558-II airplane /

Jones, Ira P.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"November 26, 1952."Includes bibliographical references (p. 8).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...

Measurements of aerodynamic heat transfer and boundary-layer transition on a 10 degree cone in free flight at supersonic mach numbers up to 5.9 /

Rumsey, Charles B.
Lee, Dorothy B.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics; Vehicle performan...

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

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 measurements and comparison with flight of the boundary layer and heat transfer on a hollow cylinder at Mach 3 /

Stallings, Robert L.
Lamb, Milton.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1980

Dec. 1980."Langley Research Center."Includes bibliographical references.Mode of access: Internet

Preliminary results from a free-flight investigation of boundary-layer transition and heat transfer on a highly polished 8-inch-diameter hemisphere-cylinder at Mach numbers up to 3 and Reynolds numbers based on a length of 1 foot up to 17.7 x 10⁶ /

Hall, James R.
Piland, Robert O.
Speegle, Katherine C.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"May 16, 1957."Includes bibliographical references (p. 11).Mode of access: Internet

Local afterbody heat transfer to a blunt two-dimensional configuration at Mach 8 /

Bushnell, Dennis M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."July 1968Includes bibliographical references (p. 21-22).Mode of access: Internet

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

Measurements of aerodynamic heat transfer in turbulent separated regions at a Mach number of 1.8 /

Abstract

Extracted data

Measurements of aerodynamic heat transfer in turbulent separated regions at a Mach number of 1.8 /

Abstract

Extracted data

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