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

Experimental thrust performance of a high-area-ratio rocket nozzle /

Pavli, Albert J.
Smith, Tamara A.
Kacynski, Kenneth J.
Lewis Research Center.

January 1987

Prepared at Lewis Research Center."April 1987"--Cover.Includes bibliographical references (p. 13).Mo...

Static internal performance of a single-engine nonaxisymmetric-nozzle vaned-thrust-reverser design with thrust modulation capabilities /

Leavitt, Laurence D.
Burley, James R.
Langley Research Center.

January 1985

Prepared at Langley Research Center."December 1985"--Cover.Includes bibliographical references (p. 1...

Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to 1.20 /

Carson, George T.
Lamb, Milton.
Langley Research Center.

January 1988

Prepared at Langley Research Center."June 1988"--Cover.Includes bibliographical references (p. 13).M...

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

Harrington, Douglas E.
Skebe, Stanley A., joint author.
Schloemer, James J., joint author.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

January 1976

Cover title.Includes bibliographical references (p. 11-13).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, D. E.
Schloemer, J. J.
Skebe, S. A.

October 1975

Plug nozzles with chute-type noise suppressors were tested with and without ejector shrouds at free-...

Flight velocity effects on jet noise of several variations of a twelve-chute suppressor installed on a plug nozzle /

Burley, Richard R.
Johns, Albert L.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17-18).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

Thrust performance of isolated, two-dimensional suppressed plug nozzles with and without ejectors at Mach numbers from 0 to 0.45

Harrington, D. E.
Schloemer, J. J.
Skebe, S. A.

May 1976

A series of two-dimensional plug nozzles was tested with and without ejector shrouds at free stream ...

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 ...

Flight velocity effects on jet noise of several variations of a 48-tube suppressor installed on a plug nozzle /

Burley, Richard R.
Head, Verlon L.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17-18).Mode of...

Performance characteristics of an isolated coannular plug nozzle at transonic speeds /

Mercer, Charles E.
Burley, James R.
Langley Research Center.

Performed by NASA Langley Research Center for the National Aeronautics and Space Administration. Per...

Thrust performance of isolated plug nozzles with two types of 40-spoke noise suppressor at Mach numbers from 0 to 0.45

Schloemer, J. J.
Harrington, D. E.

January 1974

Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers fro...

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 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...

Experimental thrust performance of a high-area-ratio rocket nozzle /

Pavli, Albert J.
Smith, Tamara A.
Kacynski, Kenneth J.
Lewis Research Center.

January 1987

Prepared at Lewis Research Center."April 1987"--Cover.Includes bibliographical references (p. 13).Mo...

Static internal performance of a single-engine nonaxisymmetric-nozzle vaned-thrust-reverser design with thrust modulation capabilities /

Leavitt, Laurence D.
Burley, James R.
Langley Research Center.

January 1985

Prepared at Langley Research Center."December 1985"--Cover.Includes bibliographical references (p. 1...

Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to 1.20 /

Carson, George T.
Lamb, Milton.
Langley Research Center.

January 1988

Prepared at Langley Research Center."June 1988"--Cover.Includes bibliographical references (p. 13).M...

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

Harrington, Douglas E.
Skebe, Stanley A., joint author.
Schloemer, James J., joint author.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

January 1976

Cover title.Includes bibliographical references (p. 11-13).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, D. E.
Schloemer, J. J.
Skebe, S. A.

October 1975

Plug nozzles with chute-type noise suppressors were tested with and without ejector shrouds at free-...

Flight velocity effects on jet noise of several variations of a twelve-chute suppressor installed on a plug nozzle /

Burley, Richard R.
Johns, Albert L.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17-18).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

Thrust performance of isolated, two-dimensional suppressed plug nozzles with and without ejectors at Mach numbers from 0 to 0.45

Harrington, D. E.
Schloemer, J. J.
Skebe, S. A.

May 1976

A series of two-dimensional plug nozzles was tested with and without ejector shrouds at free stream ...

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 ...

Flight velocity effects on jet noise of several variations of a 48-tube suppressor installed on a plug nozzle /

Burley, Richard R.
Head, Verlon L.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17-18).Mode of...

Performance characteristics of an isolated coannular plug nozzle at transonic speeds /

Mercer, Charles E.
Burley, James R.
Langley Research Center.

Performed by NASA Langley Research Center for the National Aeronautics and Space Administration. Per...

Thrust performance of isolated plug nozzles with two types of 40-spoke noise suppressor at Mach numbers from 0 to 0.45

Schloemer, J. J.
Harrington, D. E.

January 1974

Plug nozzles with two types of 40-spoke noise suppressor were tested at free-stream Mach numbers fro...

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 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...

Experimental thrust performance of a high-area-ratio rocket nozzle /

Pavli, Albert J.
Smith, Tamara A.
Kacynski, Kenneth J.
Lewis Research Center.

January 1987

Prepared at Lewis Research Center."April 1987"--Cover.Includes bibliographical references (p. 13).Mo...

Static internal performance of a single-engine nonaxisymmetric-nozzle vaned-thrust-reverser design with thrust modulation capabilities /

Leavitt, Laurence D.
Burley, James R.
Langley Research Center.

January 1985

Prepared at Langley Research Center."December 1985"--Cover.Includes bibliographical references (p. 1...

Aeropropulsive characteristics of isolated combined turbojet/ramjet nozzles at Mach numbers from 0 to 1.20 /

Carson, George T.
Lamb, Milton.
Langley Research Center.

January 1988

Prepared at Langley Research Center."June 1988"--Cover.Includes bibliographical references (p. 13).M...

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

Abstract

Extracted data

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

Abstract

Extracted data

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