Performance of experimental channeled-wall annular turbojet combustor at conditions simulating high-altitude supersonic flight.

Performance comparisons of JFC-2 and MIL-F-5624A (JP-3) fuels in tubular and annular combustors /

McCafferty, Richard J.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"January 23, 1952."Includes bibliographical references (p. 6).Mode of access: Internet

Altitude-wind-tunnel investigation of a 4000-pound-thrust axial-flow turbojet engine

Fleming, William A.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Flight Propulsion Research Laboratory.

On front cover: "August 3, 1948."Includes bibliographical references: p. 17.Mode of access: Internet

Effect of combustor-inlet conditions on performance of an annular turbojet combustor /

Childs, J. Howard.
Surine, Oakley W.
McCafferty, RIchard J.
United States. National Advisory Committee for Aeronautics.

January 1947

The combustion performance and particularly the phenomenon of altitude operational limits was studie...

Simulated altitude performance of two annular combustors with continuous axial openings for admission of primary air /

Zettle, Eugene V.
Mark, Herman, joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "August 3, 1950."Includes bibliographical references: p. 12.Mode of access: Internet

Performance investigation of can-type combustor from British turbojet engine and comparison of this combustor with can-type combustor from U.S. turbojet engine /

Cook, William P.
Koch, Richard G., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "February 28, 1950."Includes bibliographical references (p. 11).Mode of access: Inte...

Transient and steady-state performance of a single turbojet combustor with four different fuel nozzles /

McCafferty, Richard J.
Donlon, Richard H.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1955

"Declassified October 31, 1958.""October 21, 1955."Cover title.Includes bibliographical references (...

Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions /

Butze, Helmut F.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1969

Prepared at Lewis Research Center.N69-16154.Cover title.Includes bibliographical references (p. 25)....

Investigation of the performance of a turbojet engine with variable-position compressor inlet guide vanes /

Budinger, Ray E.
Kaufman, Harold R.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"October 4, 1955."Includes bibliographical references (p. 20).Mode of access: Internet

The performance of conical supersonic scoop inlets on circular fuselages /

Hasel, Lowell E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"November 17, 1953."Includes bibliographical references (p. 7).Mode of access: Internet

Turbojet combustor performance with natural gas fuel

Marchionna, Nicholas R.
Trout, Arthur M.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

Prepared at Lewis Research Center."February 1970."Cover title.Includes bibliographical references (p...

An experimental study of five annular air inlet configurations at subsonic and transonic speeds /

Bryan, Carroll R.
Fleming, Frank F.
Milillo, Jospeh R.
Pendley, Robert E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"August 19, 1953."Includes bibliographical references (p. 22-23).Mode of access: Internet

Turbojet combustor performance with injection of hydrogen peroxide for thrust augmentation /

Metzler, Allen J.
Grobman, Jack S.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1956

"Declassified October 31, 1958.""April 17, 1956."Cover title.Includes bibliographical references (p....

Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5 /

Schum, Harold J.
Nunamaker, Robert R.
Petrash, Donald A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 27).Mode of access: Internet

Investigation of two-stage air-cooled turbine suitable for flight at mach number of 2.5.

Miser, James W.
Stewart, Warner L.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1956

"October 22, 1956."Includes bibliographical references (p. 17).Mode of access: Internet

Experimental investigation of the partial- admission performance characteristics of a single-stage Mach 2 supersonic turbine /

Moffitt, Thomas P.
Klag, Frederick W.
Langley Research Center.

January 1959

"September 1959."Cover title.Includes bibliographical references (p. 8).Mode of access: Internet

Performance comparisons of JFC-2 and MIL-F-5624A (JP-3) fuels in tubular and annular combustors /

McCafferty, Richard J.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"January 23, 1952."Includes bibliographical references (p. 6).Mode of access: Internet

Altitude-wind-tunnel investigation of a 4000-pound-thrust axial-flow turbojet engine

Fleming, William A.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Flight Propulsion Research Laboratory.

On front cover: "August 3, 1948."Includes bibliographical references: p. 17.Mode of access: Internet

Effect of combustor-inlet conditions on performance of an annular turbojet combustor /

Childs, J. Howard.
Surine, Oakley W.
McCafferty, RIchard J.
United States. National Advisory Committee for Aeronautics.

January 1947

The combustion performance and particularly the phenomenon of altitude operational limits was studie...

Simulated altitude performance of two annular combustors with continuous axial openings for admission of primary air /

Zettle, Eugene V.
Mark, Herman, joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "August 3, 1950."Includes bibliographical references: p. 12.Mode of access: Internet

Performance investigation of can-type combustor from British turbojet engine and comparison of this combustor with can-type combustor from U.S. turbojet engine /

Cook, William P.
Koch, Richard G., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "February 28, 1950."Includes bibliographical references (p. 11).Mode of access: Inte...

Transient and steady-state performance of a single turbojet combustor with four different fuel nozzles /

McCafferty, Richard J.
Donlon, Richard H.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1955

"Declassified October 31, 1958.""October 21, 1955."Cover title.Includes bibliographical references (...

Performance of swirl-can turbojet combustors at simulated supersonic combustor-inlet conditions /

Butze, Helmut F.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1969

Prepared at Lewis Research Center.N69-16154.Cover title.Includes bibliographical references (p. 25)....

Investigation of the performance of a turbojet engine with variable-position compressor inlet guide vanes /

Budinger, Ray E.
Kaufman, Harold R.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"October 4, 1955."Includes bibliographical references (p. 20).Mode of access: Internet

The performance of conical supersonic scoop inlets on circular fuselages /

Hasel, Lowell E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"November 17, 1953."Includes bibliographical references (p. 7).Mode of access: Internet

Turbojet combustor performance with natural gas fuel

Marchionna, Nicholas R.
Trout, Arthur M.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

Prepared at Lewis Research Center."February 1970."Cover title.Includes bibliographical references (p...

An experimental study of five annular air inlet configurations at subsonic and transonic speeds /

Bryan, Carroll R.
Fleming, Frank F.
Milillo, Jospeh R.
Pendley, Robert E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"August 19, 1953."Includes bibliographical references (p. 22-23).Mode of access: Internet

Turbojet combustor performance with injection of hydrogen peroxide for thrust augmentation /

Metzler, Allen J.
Grobman, Jack S.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1956

"Declassified October 31, 1958.""April 17, 1956."Cover title.Includes bibliographical references (p....

Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5 /

Schum, Harold J.
Nunamaker, Robert R.
Petrash, Donald A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 27).Mode of access: Internet

Investigation of two-stage air-cooled turbine suitable for flight at mach number of 2.5.

Miser, James W.
Stewart, Warner L.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1956

"October 22, 1956."Includes bibliographical references (p. 17).Mode of access: Internet

Experimental investigation of the partial- admission performance characteristics of a single-stage Mach 2 supersonic turbine /

Moffitt, Thomas P.
Klag, Frederick W.
Langley Research Center.

January 1959

"September 1959."Cover title.Includes bibliographical references (p. 8).Mode of access: Internet

Performance comparisons of JFC-2 and MIL-F-5624A (JP-3) fuels in tubular and annular combustors /

McCafferty, Richard J.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1952

"January 23, 1952."Includes bibliographical references (p. 6).Mode of access: Internet

Altitude-wind-tunnel investigation of a 4000-pound-thrust axial-flow turbojet engine

Fleming, William A.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Flight Propulsion Research Laboratory.

On front cover: "August 3, 1948."Includes bibliographical references: p. 17.Mode of access: Internet

Effect of combustor-inlet conditions on performance of an annular turbojet combustor /

Childs, J. Howard.
Surine, Oakley W.
McCafferty, RIchard J.
United States. National Advisory Committee for Aeronautics.

January 1947

The combustion performance and particularly the phenomenon of altitude operational limits was studie...

Performance of experimental channeled-wall annular turbojet combustor at conditions simulating high-altitude supersonic flight.

Abstract

Extracted data

Performance of experimental channeled-wall annular turbojet combustor at conditions simulating high-altitude supersonic flight.

Abstract

Extracted data

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