Subsonic performance characteristics of a large-scale 1.075-pressure-ratio tip-turbine cruise-fan propulsion system /

Aerodynamic performance of a 1.25-pressure-ratio axial-flow fan stage /

Moore, Royce D.
Steinke, Ronald J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Chiefly tables.Cover title.Bibliography: p. 19.Mode of access: Int...

Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine /

Whitney, Warren J.
Behning, Frank P.
Schum, Harold J.
Lewis Research Center.

Prepared at Lewis Research Center.Cover title.Includes bibliographical references.1. Turbine design ...

Aerodynamic characteristics of a hypersonic cruise aircraft concept with wing-mounted propulsion systems at mach numbers of 2.96, 3.96, and 4.63 /

Riebe, Gregory D.
Pittman, Jimmy L.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject category 02."March 1981"--Cover."Langley Research Center."Mode of access: Internet

Subsonic Performance Characteristics of a Large-Scale 1.075-Pressure-Ratio Tip-Turbine Cruise-Fan Propulsion System

Capone, F. J.
Norton, H. T., Jr.

August 1969

Performance of turbine driven V/STOL cruise fan propulsion system at subsonic Mach number

Cruise performance of an isolated 1.15 pressure ratio turbofan propulsion system simulator at Mach numbers from 0.6 to 0.85 /

Steffen, Fred W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 22).Mode of ac...

Subsonic Aerodynamic Characteristics of a Large-Scale 1.075-Pressure-Ratio Tip-Turbine Cruise-Fan Propulsion System at Angle of Attack

Capone, Francis J.

August 1969

Wind tunnel tests of subsonic aerodynamic characteristics of large scale tip turbine cruise fan with...

Cold-air performance of compressor-drive turbine of Department of Energy upgraded automobile gas turbine engine /

Roelke, Richard J.
Haas, Jeffrey E.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Propulsion Laboratory (U.S.)
Lewis Research Center.

"October 1982"--Vol. II."Lewis Research Center.""June 1981"--Vol. I."AVRADCOM Research and Technolog...

Turbine performance in a gas-bearing Brayton cycle turboalternator /

Curreri, Joseph S.
Wood, James C.
Kruchowy, Roman.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1969

Turbine performance in gas-bearing Brayton cycle turboalternator.Includes bibliographical references...

Air-performance evaluation of a 4.0-inch-mean-diameter single-stage turbine at various inlet pressures from 0.14 to 1.88 atmospheres and corresponding Reynolds numbers from 2500 to 50,000 /

Wong, Robert Y.
Nusbaum, William J.
United States. National Aeronautics and Space Administration.

Cover title."August 1962."Power sources, supplementary; Propulsion systems, air-jet.Includes bibliog...

Aerodynamic characteristics of a large-scale V/STOL transport model with left and lift-cruise fans /

Hall, Leo P.
Kirk, Jerry V.
Hickey, David H.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."August 1967."Includes bibliographical references (p. 11).Mode of access: Internet

Aerodynamic performance of 0.5-meter-diameter, 337-meter-per-second tip speed, 1.5-pressure-ratio, single-stage fan designed for low noise aircraft engines /

Gelder, Thomas F.
Lewis, George W., Jr.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 33-34).Mode of...

Aerodynamic performance of a 1.20-pressure-ratio fan stage designed for low noise /

Lewis, George W.
Moore, Royce D., joint author.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

January 1976

Issued Oct. 1976.Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

Transient performance of a turboalternator gas-bearing system /

Wood, James C.
Asadourian, Armen S.
Curreri, Joseph S.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Experimental operation of gas-bearing turboalternator for spacecraft power supplies.Includes bibliog...

Cold-air performance of a 12.766-centimeter-tip aixial-flow cooled turbine /

Haas, Jeffrey E.
Kofskey, Milton G., joint author.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1977

Issued Sept. 1977.Includes bibliographical references.3. Effect or rotor tip clearance on overall pe...

Performance of a 1.15-pressure-ratio axial-flow fan stage with a blade tip solidity of 0.5 /

Osborn, Walter Martin, 1918-
Steinke, Ronald J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 20).Mode of ac...

Aerodynamic performance of a 1.25-pressure-ratio axial-flow fan stage /

Moore, Royce D.
Steinke, Ronald J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Chiefly tables.Cover title.Bibliography: p. 19.Mode of access: Int...

Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine /

Whitney, Warren J.
Behning, Frank P.
Schum, Harold J.
Lewis Research Center.

Prepared at Lewis Research Center.Cover title.Includes bibliographical references.1. Turbine design ...

Aerodynamic characteristics of a hypersonic cruise aircraft concept with wing-mounted propulsion systems at mach numbers of 2.96, 3.96, and 4.63 /

Riebe, Gregory D.
Pittman, Jimmy L.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject category 02."March 1981"--Cover."Langley Research Center."Mode of access: Internet

Subsonic Performance Characteristics of a Large-Scale 1.075-Pressure-Ratio Tip-Turbine Cruise-Fan Propulsion System

Capone, F. J.
Norton, H. T., Jr.

August 1969

Performance of turbine driven V/STOL cruise fan propulsion system at subsonic Mach number

Cruise performance of an isolated 1.15 pressure ratio turbofan propulsion system simulator at Mach numbers from 0.6 to 0.85 /

Steffen, Fred W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 22).Mode of ac...

Subsonic Aerodynamic Characteristics of a Large-Scale 1.075-Pressure-Ratio Tip-Turbine Cruise-Fan Propulsion System at Angle of Attack

Capone, Francis J.

August 1969

Wind tunnel tests of subsonic aerodynamic characteristics of large scale tip turbine cruise fan with...

Cold-air performance of compressor-drive turbine of Department of Energy upgraded automobile gas turbine engine /

Roelke, Richard J.
Haas, Jeffrey E.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Propulsion Laboratory (U.S.)
Lewis Research Center.

"October 1982"--Vol. II."Lewis Research Center.""June 1981"--Vol. I."AVRADCOM Research and Technolog...

Turbine performance in a gas-bearing Brayton cycle turboalternator /

Curreri, Joseph S.
Wood, James C.
Kruchowy, Roman.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1969

Turbine performance in gas-bearing Brayton cycle turboalternator.Includes bibliographical references...

Air-performance evaluation of a 4.0-inch-mean-diameter single-stage turbine at various inlet pressures from 0.14 to 1.88 atmospheres and corresponding Reynolds numbers from 2500 to 50,000 /

Wong, Robert Y.
Nusbaum, William J.
United States. National Aeronautics and Space Administration.

Cover title."August 1962."Power sources, supplementary; Propulsion systems, air-jet.Includes bibliog...

Aerodynamic characteristics of a large-scale V/STOL transport model with left and lift-cruise fans /

Hall, Leo P.
Kirk, Jerry V.
Hickey, David H.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."August 1967."Includes bibliographical references (p. 11).Mode of access: Internet

Aerodynamic performance of 0.5-meter-diameter, 337-meter-per-second tip speed, 1.5-pressure-ratio, single-stage fan designed for low noise aircraft engines /

Gelder, Thomas F.
Lewis, George W., Jr.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 33-34).Mode of...

Aerodynamic performance of a 1.20-pressure-ratio fan stage designed for low noise /

Lewis, George W.
Moore, Royce D., joint author.
United States. National Aeronautics and Space Administration.
Lewis Research Center.

January 1976

Issued Oct. 1976.Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

Transient performance of a turboalternator gas-bearing system /

Wood, James C.
Asadourian, Armen S.
Curreri, Joseph S.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1970

Experimental operation of gas-bearing turboalternator for spacecraft power supplies.Includes bibliog...

Cold-air performance of a 12.766-centimeter-tip aixial-flow cooled turbine /

Haas, Jeffrey E.
Kofskey, Milton G., joint author.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1977

Issued Sept. 1977.Includes bibliographical references.3. Effect or rotor tip clearance on overall pe...

Performance of a 1.15-pressure-ratio axial-flow fan stage with a blade tip solidity of 0.5 /

Osborn, Walter Martin, 1918-
Steinke, Ronald J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 20).Mode of ac...

Aerodynamic performance of a 1.25-pressure-ratio axial-flow fan stage /

Moore, Royce D.
Steinke, Ronald J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Chiefly tables.Cover title.Bibliography: p. 19.Mode of access: Int...

Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine /

Whitney, Warren J.
Behning, Frank P.
Schum, Harold J.
Lewis Research Center.

Prepared at Lewis Research Center.Cover title.Includes bibliographical references.1. Turbine design ...

Aerodynamic characteristics of a hypersonic cruise aircraft concept with wing-mounted propulsion systems at mach numbers of 2.96, 3.96, and 4.63 /

Riebe, Gregory D.
Pittman, Jimmy L.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject category 02."March 1981"--Cover."Langley Research Center."Mode of access: Internet

Subsonic performance characteristics of a large-scale 1.075-pressure-ratio tip-turbine cruise-fan propulsion system /

Abstract

Extracted data

Subsonic performance characteristics of a large-scale 1.075-pressure-ratio tip-turbine cruise-fan propulsion system /

Abstract

Extracted data

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