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

Cooldown characteristics of regenerative nozzle used in full-scale, cold-flow, nuclear rocket test facility /

Turney, George E.
Cox, Eileen.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."May 1967."Includes bibliographical references (57-58).Mode of access: Internet

Digital codes for design and evaluation of convectively cooled rocket nozzle with application to nuclear-type rocket /

Rohde, John E.
Derderian, George.
Duscha, Rudolph A.
United States. National Aeronautics and Space Administration.

Cover title."January 1967."Includes bibliographical references.Mode of access: Internet

Preliminary investigation of a perforated axially symmetric nozzle for varying nozzle pressure ratios /

Reshotko, Eli
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "January 14, 1953."Title from cover.Includes bibliographical references: p. 19.Mode ...

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

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

Performance investigation of a nonpumping rocket-ejector system for altitude simulation /

Fortini, Anthony.
Lewis Research Center.

Prepared at Lewis Research Center."December 1959."Cover title.Includes bibliographical references (p...

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

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...

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

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...

Investigation of installation effects on single-engine convergent-divergent nozzles /

Burley, James R.
Berrier, Bobby L.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

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

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...

Experimental study of aeroelastic instability of overexpanded rocket nozzle extensions /

Tuovila, W. J. (Weimer J.)
Land, Norman S.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 6).Mode of access: Internet

Experimental study of effects of geometric variables on performance of conical rocket - engine exhaust nozzles. /

Bloomer, Harry E.
Renas, Pqul E.
Antl, Robert J.
United States. National Aeronautics and Space Administration.

Cover title."June 1961."Aerodynamics, missiles and space vehicles; Propellants; Propulsion system el...

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

Cooldown characteristics of regenerative nozzle used in full-scale, cold-flow, nuclear rocket test facility /

Turney, George E.
Cox, Eileen.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."May 1967."Includes bibliographical references (57-58).Mode of access: Internet

Digital codes for design and evaluation of convectively cooled rocket nozzle with application to nuclear-type rocket /

Rohde, John E.
Derderian, George.
Duscha, Rudolph A.
United States. National Aeronautics and Space Administration.

Cover title."January 1967."Includes bibliographical references.Mode of access: Internet

Preliminary investigation of a perforated axially symmetric nozzle for varying nozzle pressure ratios /

Reshotko, Eli
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "January 14, 1953."Title from cover.Includes bibliographical references: p. 19.Mode ...

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

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

Performance investigation of a nonpumping rocket-ejector system for altitude simulation /

Fortini, Anthony.
Lewis Research Center.

Prepared at Lewis Research Center."December 1959."Cover title.Includes bibliographical references (p...

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

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...

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

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...

Investigation of installation effects on single-engine convergent-divergent nozzles /

Burley, James R.
Berrier, Bobby L.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

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

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...

Experimental study of aeroelastic instability of overexpanded rocket nozzle extensions /

Tuovila, W. J. (Weimer J.)
Land, Norman S.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 6).Mode of access: Internet

Experimental study of effects of geometric variables on performance of conical rocket - engine exhaust nozzles. /

Bloomer, Harry E.
Renas, Pqul E.
Antl, Robert J.
United States. National Aeronautics and Space Administration.

Cover title."June 1961."Aerodynamics, missiles and space vehicles; Propellants; Propulsion system el...

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

Cooldown characteristics of regenerative nozzle used in full-scale, cold-flow, nuclear rocket test facility /

Turney, George E.
Cox, Eileen.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."May 1967."Includes bibliographical references (57-58).Mode of access: Internet

Digital codes for design and evaluation of convectively cooled rocket nozzle with application to nuclear-type rocket /

Rohde, John E.
Derderian, George.
Duscha, Rudolph A.
United States. National Aeronautics and Space Administration.

Cover title."January 1967."Includes bibliographical references.Mode of access: Internet

Preliminary investigation of a perforated axially symmetric nozzle for varying nozzle pressure ratios /

Reshotko, Eli
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "January 14, 1953."Title from cover.Includes bibliographical references: p. 19.Mode ...

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

Abstract

Extracted data

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

Abstract

Extracted data

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