Interference heating from interactions of shock waves with turbulent boundary layers at Mach 6 /

Evaluation of some control-volume techniques for analysis of shock-boundary-layer interactions in supersonic inlets /

Hingst, Warren R.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 9).Mode of acc...

The compressible turbulent boundary layer on a blunt swept slab with and without leading-edge blowing /

Hunt, James L. (James Larry), 1939-
Beckwith, Ivan E.
Bushnell, Dennis M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

Prepared at Langley Research Center."March 1971."Cover title.Includes bibliographical references (p....

Control of shock wave - boundary layer interactions by bleed in supersonic mixed compression inlets /

Fukuda, Michael K.
Reshotko, Eli.
Hingst, Warren R.
Lewis Research Center.
Case Western Reserve University.

January 1975

Cover title.Includes bibliographical references (p. 131-133).Mode of access: Internet

Weak incident shock interactions with Mach 8 laminar boundary layers /

Kaufman, Louis G.
Johnson, Charles B.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 21-23).Mode ...

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...

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 (...

Effect of aerodynamic heating on the flutter of a rectangular wing at a mach number of 2 /

Runyan, Harry L.
Jones, Nan H.
Langley Research Center.

Prepared at the Langley Research Center, Langley Research Center.Cover title."June 1960."--Cover.Inc...

A simplified method for thermal analysis of a cowl leading edge subject to intense local shock-wave-interference heating /

McGowan, David M.
Scotti, Stephen J. (Stephen Joseph)
Camarda, Charles J.
Langley Research Center.

January 1992

Prepared at Langley Research Center.Includes bibliographical references (p. 18).Mode of access: Inte...

Effects of Mach number on pitot-probe displacment in a turbulent boundary layer /

Allen, Jerry M.
Langley Research Center.

January 1974

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

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

Experimental and predicted heating distributions for biconics at incidence in air at Mach 10 /

Miller, Charles G. (Charles George), 1940-
Langley Research Center.

January 1984

Prepared at Langley Research Center."November 1984"--Cover.Includes bibliographical references (p. 1...

Aerodynamic heating and loading within large open cavities in cone and cone-cyclinder-flare models at Mach 6.7 /

Hunt, L. Roane (Lewis Roane)
Langley Research Center.

January 1974

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

Thermal design for areas of interference heating on actively cooled hypersonic aircraft /

Herring, R. L.
Stone, J. E., joint author.
McDonnell Douglas Corporation.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1978

January 1978.Prepared for Langley Research Center under contract NAS1-14140.Includes bibliographical...

Effect of geometry variations on lee-surface vortex-induced heating for flat-bottom three-dimensional bodies at Mach 6 /

Hefner, Jerry N.
Lanley Research Center.

January 1973

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Numerical study of sound propagation in a jet flow /

Padula, Sharon L.
Liu, Chen-Huei.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 20).Mode of ...

Evaluation of some control-volume techniques for analysis of shock-boundary-layer interactions in supersonic inlets /

Hingst, Warren R.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 9).Mode of acc...

The compressible turbulent boundary layer on a blunt swept slab with and without leading-edge blowing /

Hunt, James L. (James Larry), 1939-
Beckwith, Ivan E.
Bushnell, Dennis M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

Prepared at Langley Research Center."March 1971."Cover title.Includes bibliographical references (p....

Control of shock wave - boundary layer interactions by bleed in supersonic mixed compression inlets /

Fukuda, Michael K.
Reshotko, Eli.
Hingst, Warren R.
Lewis Research Center.
Case Western Reserve University.

January 1975

Cover title.Includes bibliographical references (p. 131-133).Mode of access: Internet

Weak incident shock interactions with Mach 8 laminar boundary layers /

Kaufman, Louis G.
Johnson, Charles B.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 21-23).Mode ...

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...

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 (...

Effect of aerodynamic heating on the flutter of a rectangular wing at a mach number of 2 /

Runyan, Harry L.
Jones, Nan H.
Langley Research Center.

Prepared at the Langley Research Center, Langley Research Center.Cover title."June 1960."--Cover.Inc...

A simplified method for thermal analysis of a cowl leading edge subject to intense local shock-wave-interference heating /

McGowan, David M.
Scotti, Stephen J. (Stephen Joseph)
Camarda, Charles J.
Langley Research Center.

January 1992

Prepared at Langley Research Center.Includes bibliographical references (p. 18).Mode of access: Inte...

Effects of Mach number on pitot-probe displacment in a turbulent boundary layer /

Allen, Jerry M.
Langley Research Center.

January 1974

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

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

Experimental and predicted heating distributions for biconics at incidence in air at Mach 10 /

Miller, Charles G. (Charles George), 1940-
Langley Research Center.

January 1984

Prepared at Langley Research Center."November 1984"--Cover.Includes bibliographical references (p. 1...

Aerodynamic heating and loading within large open cavities in cone and cone-cyclinder-flare models at Mach 6.7 /

Hunt, L. Roane (Lewis Roane)
Langley Research Center.

January 1974

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

Thermal design for areas of interference heating on actively cooled hypersonic aircraft /

Herring, R. L.
Stone, J. E., joint author.
McDonnell Douglas Corporation.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1978

January 1978.Prepared for Langley Research Center under contract NAS1-14140.Includes bibliographical...

Effect of geometry variations on lee-surface vortex-induced heating for flat-bottom three-dimensional bodies at Mach 6 /

Hefner, Jerry N.
Lanley Research Center.

January 1973

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Numerical study of sound propagation in a jet flow /

Padula, Sharon L.
Liu, Chen-Huei.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 20).Mode of ...

Evaluation of some control-volume techniques for analysis of shock-boundary-layer interactions in supersonic inlets /

Hingst, Warren R.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 9).Mode of acc...

The compressible turbulent boundary layer on a blunt swept slab with and without leading-edge blowing /

Hunt, James L. (James Larry), 1939-
Beckwith, Ivan E.
Bushnell, Dennis M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1971

Prepared at Langley Research Center."March 1971."Cover title.Includes bibliographical references (p....

Control of shock wave - boundary layer interactions by bleed in supersonic mixed compression inlets /

Fukuda, Michael K.
Reshotko, Eli.
Hingst, Warren R.
Lewis Research Center.
Case Western Reserve University.

January 1975

Cover title.Includes bibliographical references (p. 131-133).Mode of access: Internet

Interference heating from interactions of shock waves with turbulent boundary layers at Mach 6 /

Abstract

Extracted data

Interference heating from interactions of shock waves with turbulent boundary layers at Mach 6 /

Abstract

Extracted data

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