Determination of local experimental heat-transfer coefficients on combustion side of an ammonia-oxygen rocket /

Experimental performance of a hydrogen-fluorine rocket engine at several chamber pressures and exhaust-nozzle expansion area ratios /

Jones, William L.
Gibb, John W.
Aukerman, Carl A.
Lewis Research Center.

January 1960

"October 1960."Cover title.Includes bibliographical references (p. 20).Mode of access: Internet

An experimental determination of the dynamic response of a long hydraulic line /

Regetz, John D.
United States. National Aeronautics and Space Administration.

Cover title."December 1960."Fluid mechanics; Propellants; Propulsion system elements; Propulsion sys...

Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle /

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

January 1987

Prepared at Lewis Research Center."August 1987"--Cover.Includes bibliographical references (p. 24).M...

Application of various techniques for determining local heat-transfer coefficients in a rocket engine from transient experimental data /

Liebert, Curt H.
Grant, Ronald W.
Hatch, James E.
Lewis Research Center.

January 1960

"NASA TN D-277.""Lewis Research Center, Cleveland, Ohio.""April 1960."Cover title.Includes bibliogra...

Boiling heat transfer to liquid hydrogen and nitrogen in forced flow /

Lewis, James P.
Kline, John F.
Goodykoontz, Jack H.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Fluid mechanics; Propellants; Propulsion system elements; Propulsion sy...

A thermodynamic analysis of thrust augmentation for nuclear rockets /

Henneberry, Hugh M.
Becker, Roger D.
Corrington, Lester C.
United States. National Aeronautics and Space Administration.

Cover title." March 1961."Propulsion systems, liquid fuel rockets; Propulsion systems, nuclear.Inclu...

Experimental performance of nozzles having area ratios up to 300 on JP-4 fuel - liquid-oxygen rocket engine. /

Lovell, J. Calvin
Samanich, Nick E.
United States. National Aeronautics and Space Administration.

Abstract:Cover title."June 1961."Aerodynamics, missiles and space vehicles; Propulsion system elemen...

Heat- and mass-transfer characteristics of an axial-flow liquid-core nuclear rocket employing radiation heat transfer /

Ragsdale, Robert G.
Donovan, Leo F.
Kascak, Albert F.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."August 1967."Includes bibliographical references (p. 31-32).Mode of access: Internet

An analysis of thermal radiation heat transfer in a nuclear-rocket nozzle /

Robbins, William H.
United States. National Aeronautics and Space Administration.

Cover title."January 1961."Propulsion systems, nuclear.Includes bibliographical references.Mode of a...

Experimental study of effects of geometric variables on performance of contoured rocket engine exhaust nozzles /

bloomer, Harry E.
Renas, Paul E.
Antl, Robert J.
United States. National Aeronautics and Space Administration.

Cover title."January 1962."Propulsion system elements; Propulsion systems, liquid-fuel.Includes bibl...

Examination of pressure oscillations induced by changes in the burning rate of flames /

Schalla, Rose L.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Chemistry, physical; Propulsion systems, liquid-fuel rockets; Propulsion sy...

Coolant-side heat-transfer rates for a hydrogen-oxygen rocket and a new technique for data correlation /

Schacht, Ralph L.
Quentmeyer, Richard J.
Lewis Research Center.

January 1973

Prepared at Lewis Research Center.Cover title.Bibliography: p. 21-22.Mode of access: Internet

Theoretical investigation of radiant heat transfer in the fuel region of a gaseous nuclear rocket engine /

Kesten, A. S.
Krascella, N. L.

"January 1967"--cover.Includes bibliographical references.Prepared by United Aircraft Corporation.Mo...

Ignition of hydrogen-oxygen rocket combustor with chlorine trifluoride and triethylaluminum /

Gregory, John W.
Straight, David M.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Materials, other; Propulsion system elements; Propulsion systems, liquid fu...

Combined effect of contraction ratio and chamber pressure on the performance of a gaseous hydrogen liquid oxygen combustor for a given propellant weight flow and oxidant fuel ratio /

Hersch, Martin.
United States. National Aeronautics and Space Administration.

Cover title."February 1961."Propulsion system elements; Propulsion systems, liquid-fuel rockets; Pro...

Experimental performance of a hydrogen-fluorine rocket engine at several chamber pressures and exhaust-nozzle expansion area ratios /

Jones, William L.
Gibb, John W.
Aukerman, Carl A.
Lewis Research Center.

January 1960

"October 1960."Cover title.Includes bibliographical references (p. 20).Mode of access: Internet

An experimental determination of the dynamic response of a long hydraulic line /

Regetz, John D.
United States. National Aeronautics and Space Administration.

Cover title."December 1960."Fluid mechanics; Propellants; Propulsion system elements; Propulsion sys...

Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle /

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

January 1987

Prepared at Lewis Research Center."August 1987"--Cover.Includes bibliographical references (p. 24).M...

Application of various techniques for determining local heat-transfer coefficients in a rocket engine from transient experimental data /

Liebert, Curt H.
Grant, Ronald W.
Hatch, James E.
Lewis Research Center.

January 1960

"NASA TN D-277.""Lewis Research Center, Cleveland, Ohio.""April 1960."Cover title.Includes bibliogra...

Boiling heat transfer to liquid hydrogen and nitrogen in forced flow /

Lewis, James P.
Kline, John F.
Goodykoontz, Jack H.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Fluid mechanics; Propellants; Propulsion system elements; Propulsion sy...

A thermodynamic analysis of thrust augmentation for nuclear rockets /

Henneberry, Hugh M.
Becker, Roger D.
Corrington, Lester C.
United States. National Aeronautics and Space Administration.

Cover title." March 1961."Propulsion systems, liquid fuel rockets; Propulsion systems, nuclear.Inclu...

Experimental performance of nozzles having area ratios up to 300 on JP-4 fuel - liquid-oxygen rocket engine. /

Lovell, J. Calvin
Samanich, Nick E.
United States. National Aeronautics and Space Administration.

Abstract:Cover title."June 1961."Aerodynamics, missiles and space vehicles; Propulsion system elemen...

Heat- and mass-transfer characteristics of an axial-flow liquid-core nuclear rocket employing radiation heat transfer /

Ragsdale, Robert G.
Donovan, Leo F.
Kascak, Albert F.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."August 1967."Includes bibliographical references (p. 31-32).Mode of access: Internet

An analysis of thermal radiation heat transfer in a nuclear-rocket nozzle /

Robbins, William H.
United States. National Aeronautics and Space Administration.

Cover title."January 1961."Propulsion systems, nuclear.Includes bibliographical references.Mode of a...

Experimental study of effects of geometric variables on performance of contoured rocket engine exhaust nozzles /

bloomer, Harry E.
Renas, Paul E.
Antl, Robert J.
United States. National Aeronautics and Space Administration.

Cover title."January 1962."Propulsion system elements; Propulsion systems, liquid-fuel.Includes bibl...

Examination of pressure oscillations induced by changes in the burning rate of flames /

Schalla, Rose L.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Chemistry, physical; Propulsion systems, liquid-fuel rockets; Propulsion sy...

Coolant-side heat-transfer rates for a hydrogen-oxygen rocket and a new technique for data correlation /

Schacht, Ralph L.
Quentmeyer, Richard J.
Lewis Research Center.

January 1973

Prepared at Lewis Research Center.Cover title.Bibliography: p. 21-22.Mode of access: Internet

Theoretical investigation of radiant heat transfer in the fuel region of a gaseous nuclear rocket engine /

Kesten, A. S.
Krascella, N. L.

"January 1967"--cover.Includes bibliographical references.Prepared by United Aircraft Corporation.Mo...

Ignition of hydrogen-oxygen rocket combustor with chlorine trifluoride and triethylaluminum /

Gregory, John W.
Straight, David M.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Materials, other; Propulsion system elements; Propulsion systems, liquid fu...

Combined effect of contraction ratio and chamber pressure on the performance of a gaseous hydrogen liquid oxygen combustor for a given propellant weight flow and oxidant fuel ratio /

Hersch, Martin.
United States. National Aeronautics and Space Administration.

Cover title."February 1961."Propulsion system elements; Propulsion systems, liquid-fuel rockets; Pro...

Experimental performance of a hydrogen-fluorine rocket engine at several chamber pressures and exhaust-nozzle expansion area ratios /

Jones, William L.
Gibb, John W.
Aukerman, Carl A.
Lewis Research Center.

January 1960

"October 1960."Cover title.Includes bibliographical references (p. 20).Mode of access: Internet

An experimental determination of the dynamic response of a long hydraulic line /

Regetz, John D.
United States. National Aeronautics and Space Administration.

Cover title."December 1960."Fluid mechanics; Propellants; Propulsion system elements; Propulsion sys...

Experimental evaluation of heat transfer on a 1030:1 area ratio rocket nozzle /

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

January 1987

Prepared at Lewis Research Center."August 1987"--Cover.Includes bibliographical references (p. 24).M...

Determination of local experimental heat-transfer coefficients on combustion side of an ammonia-oxygen rocket /

Abstract

Extracted data

Determination of local experimental heat-transfer coefficients on combustion side of an ammonia-oxygen rocket /

Abstract

Extracted data

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