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

Supersonic aerodynamics of delta wings /

Wood, Richard M.
Langley Research Center.

January 1988

Prepared at Langley Research Center."March 1988"--Cover.Includes bibliographical references (p. 22-2...

Fluctuating pressures on fan blades of a turbofan engine : flight test investigation /

Schoenster, James A.
Langley Research Center.

January 1985

Prepared at Langley Research Center."February 1985"--Cover.Includes bibliographical references (p. 7...

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

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 (...

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

Aerothermal performance of a radiatively and actively cooled panel at Mach 6.6 /

Shore, Charles P.
Weinstein, Irving.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

Subject category 34."December 1979"--Cover.Includes bibliographical references.Mode of access: Inter...

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

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...

Aerothermal environment in chordwise gaps between split elevons at Mach 6.8 /

Hunt, L. Roane (Lewis Roane)
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

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 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...

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 ...

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...

Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 /

Cubbison, Robert W.
Ward, James J.
Anderson, Bernhard H.
Lewis Research Center.

Prepared at Lewis Research Center."February 1961."Cover title.Includes bibliographical references (p...

Supersonic aerodynamics of delta wings /

Wood, Richard M.
Langley Research Center.

January 1988

Prepared at Langley Research Center."March 1988"--Cover.Includes bibliographical references (p. 22-2...

Fluctuating pressures on fan blades of a turbofan engine : flight test investigation /

Schoenster, James A.
Langley Research Center.

January 1985

Prepared at Langley Research Center."February 1985"--Cover.Includes bibliographical references (p. 7...

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

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 (...

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

Aerothermal performance of a radiatively and actively cooled panel at Mach 6.6 /

Shore, Charles P.
Weinstein, Irving.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

Subject category 34."December 1979"--Cover.Includes bibliographical references.Mode of access: Inter...

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

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...

Aerothermal environment in chordwise gaps between split elevons at Mach 6.8 /

Hunt, L. Roane (Lewis Roane)
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

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 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...

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 ...

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...

Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 /

Cubbison, Robert W.
Ward, James J.
Anderson, Bernhard H.
Lewis Research Center.

Prepared at Lewis Research Center."February 1961."Cover title.Includes bibliographical references (p...

Supersonic aerodynamics of delta wings /

Wood, Richard M.
Langley Research Center.

January 1988

Prepared at Langley Research Center."March 1988"--Cover.Includes bibliographical references (p. 22-2...

Fluctuating pressures on fan blades of a turbofan engine : flight test investigation /

Schoenster, James A.
Langley Research Center.

January 1985

Prepared at Langley Research Center."February 1985"--Cover.Includes bibliographical references (p. 7...

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

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

Abstract

Extracted data

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

Abstract

Extracted data

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