Overall and blade-element performance of a 1.20-pressure-ratio fan stage at design blade setting angle /

Aerodynamic performance of axial-flow fan stage operated at nine inlet guide vane angles /

Moore, Royce D.
Reid, Lonnie.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

"September 1979"--Cover.Includes bibliographical references (p. 12).Mode of access: Internet

Highly loaded multi-stage fan drive turbine-tandem blade configuration design /

Evans, D. C.
Wolfmeyer, G. W.
Lewis Research Center.
General Electric Company.

January 1972

"Prepared by General Electric Company ... for Lewis Research Center."Cover title.Bibliography: p. 14...

Overall and blade element performance of a 1.20 pressure ratio fan stage with rotor blades reset -7 ̊ /

Lewis, George W., Jr.
Kovich, George, joint author.
Lewis Research Center.

January 1976

A 51-cm-diam model of a fan stage for short haul aircraft was tested in a single stage compressor re...

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...

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

Aerodynamic performance of 1.38-pressure-ratio, variable-pitch fan stage /

Moore, Royce D.
Osborn, Walter Martin, 1918-
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

"September 1979"--Cover."Lewis Research Center."Includes bibliographical references (p. 19).Mode of ...

Performance of a 1.57-pressure-ratio transonic fan stage with a screen-induced 90 ̊circumferential inlet flow distribution /

Sanger, Nelson L.
Lewis Research Center.

January 1976

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 28).Mode of ac...

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...

Performance of a highly loaded two-stage axial-flow fan /

Ruggeri, Robert S.
Benser, William A.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Chiefly tables.Cover title.Mode of access: Internet

Highly loaded multi-stage fan drive turbine : performance of final three configurations /

Cherry, D. G.
Thomas, M. W.
Lewis Research Center.
General Electric Company.

January 1974

"Prepared by General Electric Company ... for Lewis Research Center."Cover title.Includes bibliograp...

Overall and blade element performance of a 1.20-pressure-ratio fan stage with rotor blades reset -5 ̊ /

Lewis, George W., Jr.
Moore, Royce D., joint author.
Osborn, Walter Martin, 1918- joint author.
Lewis Research Center.

January 1976

A 51-cm-diam model of a fan stage for a short haul aircraft was tested in a single stage-compressor ...

Acoustic and aerodynamic performance of a 1.83-meter- (6-ft-) diameter 1.2-pressure-ratio fan (QF-6) /

Woodward, Richard P.
Stakolich, Edward G.
Lucas, James G.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 23-24).Mode of...

Performance of two-stage fan with larger dampers on first-stage rotor /

Urasek, Donald C.
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

"May 1979"--Cover."Lewis Research Center."Includes bibliographical references.Mode of access: Intern...

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 performance of axial-flow fan stage operated at nine inlet guide vane angles /

Moore, Royce D.
Reid, Lonnie.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

"September 1979"--Cover.Includes bibliographical references (p. 12).Mode of access: Internet

Highly loaded multi-stage fan drive turbine-tandem blade configuration design /

Evans, D. C.
Wolfmeyer, G. W.
Lewis Research Center.
General Electric Company.

January 1972

"Prepared by General Electric Company ... for Lewis Research Center."Cover title.Bibliography: p. 14...

Overall and blade element performance of a 1.20 pressure ratio fan stage with rotor blades reset -7 ̊ /

Lewis, George W., Jr.
Kovich, George, joint author.
Lewis Research Center.

January 1976

A 51-cm-diam model of a fan stage for short haul aircraft was tested in a single stage compressor re...

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...

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

Aerodynamic performance of 1.38-pressure-ratio, variable-pitch fan stage /

Moore, Royce D.
Osborn, Walter Martin, 1918-
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

"September 1979"--Cover."Lewis Research Center."Includes bibliographical references (p. 19).Mode of ...

Performance of a 1.57-pressure-ratio transonic fan stage with a screen-induced 90 ̊circumferential inlet flow distribution /

Sanger, Nelson L.
Lewis Research Center.

January 1976

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 28).Mode of ac...

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...

Performance of a highly loaded two-stage axial-flow fan /

Ruggeri, Robert S.
Benser, William A.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Chiefly tables.Cover title.Mode of access: Internet

Highly loaded multi-stage fan drive turbine : performance of final three configurations /

Cherry, D. G.
Thomas, M. W.
Lewis Research Center.
General Electric Company.

January 1974

"Prepared by General Electric Company ... for Lewis Research Center."Cover title.Includes bibliograp...

Overall and blade element performance of a 1.20-pressure-ratio fan stage with rotor blades reset -5 ̊ /

Lewis, George W., Jr.
Moore, Royce D., joint author.
Osborn, Walter Martin, 1918- joint author.
Lewis Research Center.

January 1976

A 51-cm-diam model of a fan stage for a short haul aircraft was tested in a single stage-compressor ...

Acoustic and aerodynamic performance of a 1.83-meter- (6-ft-) diameter 1.2-pressure-ratio fan (QF-6) /

Woodward, Richard P.
Stakolich, Edward G.
Lucas, James G.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 23-24).Mode of...

Performance of two-stage fan with larger dampers on first-stage rotor /

Urasek, Donald C.
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

"May 1979"--Cover."Lewis Research Center."Includes bibliographical references.Mode of access: Intern...

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 performance of axial-flow fan stage operated at nine inlet guide vane angles /

Moore, Royce D.
Reid, Lonnie.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

"September 1979"--Cover.Includes bibliographical references (p. 12).Mode of access: Internet

Highly loaded multi-stage fan drive turbine-tandem blade configuration design /

Evans, D. C.
Wolfmeyer, G. W.
Lewis Research Center.
General Electric Company.

January 1972

"Prepared by General Electric Company ... for Lewis Research Center."Cover title.Bibliography: p. 14...

Overall and blade element performance of a 1.20 pressure ratio fan stage with rotor blades reset -7 ̊ /

Lewis, George W., Jr.
Kovich, George, joint author.
Lewis Research Center.

January 1976

A 51-cm-diam model of a fan stage for short haul aircraft was tested in a single stage compressor re...

Overall and blade-element performance of a 1.20-pressure-ratio fan stage at design blade setting angle /

Abstract

Extracted data

Overall and blade-element performance of a 1.20-pressure-ratio fan stage at design blade setting angle /

Abstract

Extracted data

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