Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0.45 /

Transonic off-design performance of a fixed divergent ejector designed for a mach number of 2.0 /

Norton, Harry T.
Mercer, Charles E.
Cassetti, Marlowe D.
United States. National Aeronautics and Space Administration.

"December 1959."Cover title.Includes bibliographical references (p. 15).Mode of access: Internet

Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 /

Bowditch, David N.
Tabata, William K.
Anderson, Bernhard H.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Preliminary investigation of off-design performance of divergent-ejector-type rocket nozzles /

Gertsma, Laurence W.
Yeager, Richard A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1960

"March 1960."Cover title.Includes bibliographical references (p. 15).Mode of access: Internet

Thrust performance of isolated 36-chute suppressor plug nozzles with and without ejectors at Mach numbers from 0 to 0.45 /

Harrington, Douglas E.
Skebe, Stanley A. (Stanley Andrew)
Schloemer, James J.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 12-14).Mode of...

Performance of an isolated two-dimensional wedge nozzle with fixed cowl and variable wedge centerbody at mach numbers up to 2.01 /

Maiden, Donald L.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1976

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

Performance of a variable divergent-shroud ejector nozzle designed for flight mach numbers up to 3.0 /

Stofan, Andrew J.
Mihaloew, James R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1961

"January 1961."Cover title.Includes bibliographical references (p. 7).Mode of access: Internet

Performance of an isolated two-dimensional variable-geometry wedge nozzle with translating shroud and collapsing wedge at speeds up to Mach 2.01 /

Maiden, Donald L.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ...

Characteristics of five ejector configurations at free-stream mach numbers from 0 to 2.0 /

Klann, John L.
Huff, Ronald G.
United States. National Aeronautics and Space Administration.

"August 1959."Cover title.Includes bibliographical references (p. 11).Mode of access: Internet

Internal performance of two nozzles utilizing gimbal concepts for thrust vectoring /

Berrier, Bobby L.
Taylor, John G. (John Gilbert)
Langley Research Center.

January 1990

Prepared at Langley Research Center.Bibliography: p. 9-10.Mode of access: Internet

Static performance of nonaxisymmetric nozzles with yaw thrust-vectoring vanes /

Mason, Mary L.
Berrier, Bobby L.
Langley Research Center.

January 1988

Prepared at Langley Research Center."May 1988"--Cover.Includes bibliographical references (p. 10).Mo...

Static internal performance including thrust vectoring and reversing of tow-dimensional convergent-divergent nozzles /

Re, Richard J.
Leavitt, Laurence D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1984

"February 1984"--Cover.Includes bibliographical references.Mode of access: Internet

Static performance of an axisymmetric nozzle with post-exit vanes for multiaxis thrust vectoring /

Berrier, Bobby L.
Langley Research Center.

January 1988

Prepared at Langley Research Center."May 1988"--Cover.Includes bibliographical references (p. 11).Mo...

Static performance of a cruciform nozzle with multiaxis thrust-vectoring and reverse-thrust capabilities /

Wing, David J.
Asbury, Scott C.
Langley Research Center.

January 1992

Prepared at Langley Research Center.Includes bibliographical references (p. 10-11).Mode of access: I...

Static internal performance characteristics of two thrust-reverser concepts for axisymmetric nozzles /

Leavitt, Laurence D.
Re, Richard J.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1982

Subject Category 02."Langley Research Center.""June 1982"--Cover.Includes bibliographical references...

Static internal performance of a two-dimensional convergent-divergent nozzle with thrust vectoring /

Bare, E. Ann.
Reubush, David E.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1987

"July 1987"--Cover.Includes bibliographical references (p. 11-12).Mode of access: Internet

Transonic off-design performance of a fixed divergent ejector designed for a mach number of 2.0 /

Norton, Harry T.
Mercer, Charles E.
Cassetti, Marlowe D.
United States. National Aeronautics and Space Administration.

"December 1959."Cover title.Includes bibliographical references (p. 15).Mode of access: Internet

Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 /

Bowditch, David N.
Tabata, William K.
Anderson, Bernhard H.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Preliminary investigation of off-design performance of divergent-ejector-type rocket nozzles /

Gertsma, Laurence W.
Yeager, Richard A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1960

"March 1960."Cover title.Includes bibliographical references (p. 15).Mode of access: Internet

Thrust performance of isolated 36-chute suppressor plug nozzles with and without ejectors at Mach numbers from 0 to 0.45 /

Harrington, Douglas E.
Skebe, Stanley A. (Stanley Andrew)
Schloemer, James J.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 12-14).Mode of...

Performance of an isolated two-dimensional wedge nozzle with fixed cowl and variable wedge centerbody at mach numbers up to 2.01 /

Maiden, Donald L.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1976

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

Performance of a variable divergent-shroud ejector nozzle designed for flight mach numbers up to 3.0 /

Stofan, Andrew J.
Mihaloew, James R.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1961

"January 1961."Cover title.Includes bibliographical references (p. 7).Mode of access: Internet

Performance of an isolated two-dimensional variable-geometry wedge nozzle with translating shroud and collapsing wedge at speeds up to Mach 2.01 /

Maiden, Donald L.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ...

Characteristics of five ejector configurations at free-stream mach numbers from 0 to 2.0 /

Klann, John L.
Huff, Ronald G.
United States. National Aeronautics and Space Administration.

"August 1959."Cover title.Includes bibliographical references (p. 11).Mode of access: Internet

Internal performance of two nozzles utilizing gimbal concepts for thrust vectoring /

Berrier, Bobby L.
Taylor, John G. (John Gilbert)
Langley Research Center.

January 1990

Prepared at Langley Research Center.Bibliography: p. 9-10.Mode of access: Internet

Static performance of nonaxisymmetric nozzles with yaw thrust-vectoring vanes /

Mason, Mary L.
Berrier, Bobby L.
Langley Research Center.

January 1988

Prepared at Langley Research Center."May 1988"--Cover.Includes bibliographical references (p. 10).Mo...

Static internal performance including thrust vectoring and reversing of tow-dimensional convergent-divergent nozzles /

Re, Richard J.
Leavitt, Laurence D.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1984

"February 1984"--Cover.Includes bibliographical references.Mode of access: Internet

Static performance of an axisymmetric nozzle with post-exit vanes for multiaxis thrust vectoring /

Berrier, Bobby L.
Langley Research Center.

January 1988

Prepared at Langley Research Center."May 1988"--Cover.Includes bibliographical references (p. 11).Mo...

Static performance of a cruciform nozzle with multiaxis thrust-vectoring and reverse-thrust capabilities /

Wing, David J.
Asbury, Scott C.
Langley Research Center.

January 1992

Prepared at Langley Research Center.Includes bibliographical references (p. 10-11).Mode of access: I...

Static internal performance characteristics of two thrust-reverser concepts for axisymmetric nozzles /

Leavitt, Laurence D.
Re, Richard J.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1982

Subject Category 02."Langley Research Center.""June 1982"--Cover.Includes bibliographical references...

Static internal performance of a two-dimensional convergent-divergent nozzle with thrust vectoring /

Bare, E. Ann.
Reubush, David E.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1987

"July 1987"--Cover.Includes bibliographical references (p. 11-12).Mode of access: Internet

Transonic off-design performance of a fixed divergent ejector designed for a mach number of 2.0 /

Norton, Harry T.
Mercer, Charles E.
Cassetti, Marlowe D.
United States. National Aeronautics and Space Administration.

"December 1959."Cover title.Includes bibliographical references (p. 15).Mode of access: Internet

Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 /

Bowditch, David N.
Tabata, William K.
Anderson, Bernhard H.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Preliminary investigation of off-design performance of divergent-ejector-type rocket nozzles /

Gertsma, Laurence W.
Yeager, Richard A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1960

"March 1960."Cover title.Includes bibliographical references (p. 15).Mode of access: Internet

Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0.45 /

Abstract

Extracted data

Thrust performance of isolated two dimension suppressed plug nozzles with and without ejectors at mach numbers from 0 to 0.45 /

Abstract

Extracted data

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