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

Effect on fan flow characteristics of length and axial location of a cascade thrust reverser /

Dietrich, Donald A. (Donald Arthur), 1943-
Kelm, Gary G.
Crooker, Andrew J. (Andrew Jackson), 1939-
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 15).Mode of ac...

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...

Performance of two-stage fan with a first-state rotor redesigned to account for the presence of a part-span damper /

Gorrell, William T.
Urasek, Donald C.
Propulsion Laboratory (U.S.)
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

Includes statistical tables."Propulsion Laboratory, "AVRADCOM Research and Technology Laboratories."...

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...

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...

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

Lewis, George W., Jr.
Tysl, Edward R.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 16).Mode of ac...

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...

Stalled and stall-free performance of axial-flow compressor stage with three inlet-guide-vane and stator-blade settings /

Urasek, Donald C.
Cunnan, Walter S.
Steinke, Ronald J.
Lewis Research Center.

January 1977

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 13).Mode of ac...

Performance of inlet stage of transonic compressor /

Urasek, Donald C.
Lewis, George W., Jr.
Steinke, Ronald J.
Lewis Research Center.

January 1976

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

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...

Highly loaded multi-stage fan drive turbine : performance of initial seven configurations /

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

January 1974

"Prepared by General Electric Company ... for Lewis Research Center."Cover title.Bibliography: p. 37...

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...

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 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

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 ...

Effect on fan flow characteristics of length and axial location of a cascade thrust reverser /

Dietrich, Donald A. (Donald Arthur), 1943-
Kelm, Gary G.
Crooker, Andrew J. (Andrew Jackson), 1939-
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 15).Mode of ac...

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...

Performance of two-stage fan with a first-state rotor redesigned to account for the presence of a part-span damper /

Gorrell, William T.
Urasek, Donald C.
Propulsion Laboratory (U.S.)
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

Includes statistical tables."Propulsion Laboratory, "AVRADCOM Research and Technology Laboratories."...

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...

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...

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

Lewis, George W., Jr.
Tysl, Edward R.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 16).Mode of ac...

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...

Stalled and stall-free performance of axial-flow compressor stage with three inlet-guide-vane and stator-blade settings /

Urasek, Donald C.
Cunnan, Walter S.
Steinke, Ronald J.
Lewis Research Center.

January 1977

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 13).Mode of ac...

Performance of inlet stage of transonic compressor /

Urasek, Donald C.
Lewis, George W., Jr.
Steinke, Ronald J.
Lewis Research Center.

January 1976

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

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...

Highly loaded multi-stage fan drive turbine : performance of initial seven configurations /

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

January 1974

"Prepared by General Electric Company ... for Lewis Research Center."Cover title.Bibliography: p. 37...

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...

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 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

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 ...

Effect on fan flow characteristics of length and axial location of a cascade thrust reverser /

Dietrich, Donald A. (Donald Arthur), 1943-
Kelm, Gary G.
Crooker, Andrew J. (Andrew Jackson), 1939-
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 15).Mode of ac...

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...

Performance of two-stage fan with a first-state rotor redesigned to account for the presence of a part-span damper /

Gorrell, William T.
Urasek, Donald C.
Propulsion Laboratory (U.S.)
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1979

Includes statistical tables."Propulsion Laboratory, "AVRADCOM Research and Technology Laboratories."...

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

Abstract

Extracted data

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

Abstract

Extracted data

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