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

Effect of properties of primary fluid on performance of cylindrical shroud ejectors /

Kochendorfer, Fred D.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "March 11, 1954."Title from cover.Includes bibliographical references: p. 16.Mode of...

Flight tests of a twin-duct induction system for a mach number range of 0.78 to 2.07 /

Nugent, Jack.
Powers, Bruce G.
United States. National Aeronautics and Space Administration.

"September 1960."Cover title.Includes bibliographical references (p. 14).Mode of access: Internet

Aerodynamic characteristics of parachutes at mach numbers from 1.6 to 3 /

Maynard, Julian D.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aircraft safety and noise.Includes bibliographical references.Mode of access:...

Internal performance of several divergent-shroud ejector nozzles with high divergence angles /

Trout, Arthur M.
Povolny, John H.
Papell, S. Stephen.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"October 2, 1957."Includes bibliographical references (p. 21-22).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

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

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

Note on performance of aircraft ejector nozzles at high secondary flows /

Kochendorfer, Fred D.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "August 27, 1954."Title from cover.Includes bibliographical references: p. 9.Mode of...

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 ...

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

Investigation at transonic speeds of a fixed divergent ejector installed in a single-engine fighter model /

Swihart, John M.
Mercer, Charles E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"March 3, 1958."Includes bibliographical references (p. 12).Mode of access: Internet

An evaluation of two cooling-air ejectors in flight at transonic speeds /

Rolls, L. Stewart
Havill, C. Dewey, joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

On front cover: "March 15, 1954."Includes bibliographical references.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

Effect of nozzle and vertical-tail variables on the performance of a three-surface F-15 model at transonic Mach numbers /

Pendergraft, Odis C.
Bare, E. Ann.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

"August 1982"--Cover.Includes bibliographical references.Mode of access: Internet

Feasibility of optimizing nozzle performance for orbital-launch nuclear rockets

Jack, John R.
United States. National Aeronautics and Space Administration.

Cover title."April 1963."Includes bibliographical references.Mode of access: Internet

Effect of properties of primary fluid on performance of cylindrical shroud ejectors /

Kochendorfer, Fred D.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "March 11, 1954."Title from cover.Includes bibliographical references: p. 16.Mode of...

Flight tests of a twin-duct induction system for a mach number range of 0.78 to 2.07 /

Nugent, Jack.
Powers, Bruce G.
United States. National Aeronautics and Space Administration.

"September 1960."Cover title.Includes bibliographical references (p. 14).Mode of access: Internet

Aerodynamic characteristics of parachutes at mach numbers from 1.6 to 3 /

Maynard, Julian D.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aircraft safety and noise.Includes bibliographical references.Mode of access:...

Internal performance of several divergent-shroud ejector nozzles with high divergence angles /

Trout, Arthur M.
Povolny, John H.
Papell, S. Stephen.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"October 2, 1957."Includes bibliographical references (p. 21-22).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

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

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

Note on performance of aircraft ejector nozzles at high secondary flows /

Kochendorfer, Fred D.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "August 27, 1954."Title from cover.Includes bibliographical references: p. 9.Mode of...

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 ...

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

Investigation at transonic speeds of a fixed divergent ejector installed in a single-engine fighter model /

Swihart, John M.
Mercer, Charles E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1958

"March 3, 1958."Includes bibliographical references (p. 12).Mode of access: Internet

An evaluation of two cooling-air ejectors in flight at transonic speeds /

Rolls, L. Stewart
Havill, C. Dewey, joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

On front cover: "March 15, 1954."Includes bibliographical references.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

Effect of nozzle and vertical-tail variables on the performance of a three-surface F-15 model at transonic Mach numbers /

Pendergraft, Odis C.
Bare, E. Ann.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

"August 1982"--Cover.Includes bibliographical references.Mode of access: Internet

Feasibility of optimizing nozzle performance for orbital-launch nuclear rockets

Jack, John R.
United States. National Aeronautics and Space Administration.

Cover title."April 1963."Includes bibliographical references.Mode of access: Internet

Effect of properties of primary fluid on performance of cylindrical shroud ejectors /

Kochendorfer, Fred D.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "March 11, 1954."Title from cover.Includes bibliographical references: p. 16.Mode of...

Flight tests of a twin-duct induction system for a mach number range of 0.78 to 2.07 /

Nugent, Jack.
Powers, Bruce G.
United States. National Aeronautics and Space Administration.

"September 1960."Cover title.Includes bibliographical references (p. 14).Mode of access: Internet

Aerodynamic characteristics of parachutes at mach numbers from 1.6 to 3 /

Maynard, Julian D.
United States. National Aeronautics and Space Administration.

Cover title."May 1961."Aircraft safety and noise.Includes bibliographical references.Mode of access:...

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

Abstract

Extracted data

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

Abstract

Extracted data

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