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

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 ...

A parametric study of effect of forebody shape on flow angularity at Mach 8 /

Johnson, Charles B.
Marcum, Don C.
Langley Research Center.

January 1974

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

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 (...

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

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

Garland, Benjamine J.
Hall, James R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"February 20, 1958."Includes bibliographical references (p. 7).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 measurements for Mach five flows over a blunt pyramidal configuration with aerodynamic controls : part of an investigation of hypersonic flow separation and control characteristics /

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

"January 1964."Includes bibliographical references (page 5).Air Force Contract No.Mode of access: In...

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

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

Experimental investigation at Mach 8 of the effects of projections and cavities on heat transfer to a model of the Viking aeroshell /

Creel, Theodore R.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 7).Mode of a...

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

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

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...

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...

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 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 ...

A parametric study of effect of forebody shape on flow angularity at Mach 8 /

Johnson, Charles B.
Marcum, Don C.
Langley Research Center.

January 1974

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

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 (...

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

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

Garland, Benjamine J.
Hall, James R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"February 20, 1958."Includes bibliographical references (p. 7).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 measurements for Mach five flows over a blunt pyramidal configuration with aerodynamic controls : part of an investigation of hypersonic flow separation and control characteristics /

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

"January 1964."Includes bibliographical references (page 5).Air Force Contract No.Mode of access: In...

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

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

Experimental investigation at Mach 8 of the effects of projections and cavities on heat transfer to a model of the Viking aeroshell /

Creel, Theodore R.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 7).Mode of a...

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

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

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...

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...

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 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 ...

A parametric study of effect of forebody shape on flow angularity at Mach 8 /

Johnson, Charles B.
Marcum, Don C.
Langley Research Center.

January 1974

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

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 (...

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

Abstract

Extracted data

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

Abstract

Extracted data

Topics

Related items

Topics

Related items