Rotating stall investigation of the 0.72 hub-tip ratio single-stage compressor /

Performance of external-compression bump inlet at Mach numbers of 1.5 to 2.0 /

Simon, Paul C.
Huff, Ronald G.
Brown, Dennis W.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"April 24, 1957."Includes bibliographical references (p. 9).Mode of access: Internet

Evaluation of a compressor bleed system for rim cooling the turbine wheel of a turbojet engine /

Morse, C. R.
Kemp, R. H.
United States. National Advisory Committee for Aeronautics.

"Declassified February 10, 1959.""March 22, 1954."Cover title.Includes bibliographical references (p...

The performance of conical supersonic scoop inlets on circular fuselages /

Hasel, Lowell E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"November 17, 1953."Includes bibliographical references (p. 7).Mode of access: Internet

Research on rotating stall in axial flow compressors.

Moore, F. K.
Armed Services Technical Information Agency (U.S.)
Wright Air Development Center.

"January 1959."Includes bibliographical references (p. 16).Mode of access: Internet

Investigation of an impulse axial-flow compressor /

Erwin, John R.
Schulze, Wallace M.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1950

"February 8, 1950."Includes bibliographical references (p. 22).Mode of access: Internet

Compressor-blade vibration and performance in a J47-23 turbojet engine under conditions of rotating stall /

Hanson, Morgan P.
Meyer, Andre J.
Johnson, Donald F.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1955

"June 13 1955."Includes bibliographical references (p. 7-8).Mode of access: Internet

Investigation of the performance of a turbojet engine with variable-position compressor inlet guide vanes /

Budinger, Ray E.
Kaufman, Harold R.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"October 4, 1955."Includes bibliographical references (p. 20).Mode of access: Internet

Investigation of an impulse axial-flow compressor rotor over a range of blade angles /

Schulze, Wallace M.
Westphal, Willard R.
Erwin, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1950

"August 29, 1950."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study.

Rohlik, Harold E.
Scibbe, Herbert W.
Wintucky, William T.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1957

"January 9, 1957."Includes bibliographical references (p. 13-14).Mode of access: Internet

Low-speed cascade investigation of loaded leading-edge compressor blades /

Emery, James C.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1956

"January 11, 1956."Includes bibliographical references (p. 11).Mode of access: Internet

Compressor-blade vibration of a J57-P-1 turbojet engine during exploratory operation with inlet-pressure distortions /

Hanson, Morgan P.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"December 23,1955."Includes bibliographical references (p. 11).Mode of access: Internet

Experimental investigation of a transonic axial-flow-compressor rotor with double-circular-arc airfoil blade sections.

Lewis, George W., Jr.
Serovy, G. K. (George K.)
Schwenk, Francis C.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

"Declassified October 31, 1958.""April 5, 1954."Cover title.Includes bibliographical references (p. ...

Vibration survey of blades in 10-stage axial-flow compressor

Meyer, Andre J. Jr.
Calvert, Howard F., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "January 31, 1949."Includes bibliographical references: p. 6.Mode of access: Interne...

Experimental investigation of an axial-flow supersonic compressor having sharp leading-edge blades with an 8-percent mean thickness-chord ratio /

Goldberg, Theodore J.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"February 4, 1955."Includes bibliographical references (p. 12).Mode of access: Internet

Preliminary investigation of hollow-bladed turbines having closed and open blade tips /

Smith, Gordon T.
Hickel, Robert O.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"August 16, 1955."Includes bibliographical references (p. 10).Mode of access: Internet

Performance of external-compression bump inlet at Mach numbers of 1.5 to 2.0 /

Simon, Paul C.
Huff, Ronald G.
Brown, Dennis W.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"April 24, 1957."Includes bibliographical references (p. 9).Mode of access: Internet

Evaluation of a compressor bleed system for rim cooling the turbine wheel of a turbojet engine /

Morse, C. R.
Kemp, R. H.
United States. National Advisory Committee for Aeronautics.

"Declassified February 10, 1959.""March 22, 1954."Cover title.Includes bibliographical references (p...

The performance of conical supersonic scoop inlets on circular fuselages /

Hasel, Lowell E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"November 17, 1953."Includes bibliographical references (p. 7).Mode of access: Internet

Research on rotating stall in axial flow compressors.

Moore, F. K.
Armed Services Technical Information Agency (U.S.)
Wright Air Development Center.

"January 1959."Includes bibliographical references (p. 16).Mode of access: Internet

Investigation of an impulse axial-flow compressor /

Erwin, John R.
Schulze, Wallace M.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1950

"February 8, 1950."Includes bibliographical references (p. 22).Mode of access: Internet

Compressor-blade vibration and performance in a J47-23 turbojet engine under conditions of rotating stall /

Hanson, Morgan P.
Meyer, Andre J.
Johnson, Donald F.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1955

"June 13 1955."Includes bibliographical references (p. 7-8).Mode of access: Internet

Investigation of the performance of a turbojet engine with variable-position compressor inlet guide vanes /

Budinger, Ray E.
Kaufman, Harold R.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"October 4, 1955."Includes bibliographical references (p. 20).Mode of access: Internet

Investigation of an impulse axial-flow compressor rotor over a range of blade angles /

Schulze, Wallace M.
Westphal, Willard R.
Erwin, John R.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1950

"August 29, 1950."Cover title.Includes bibliographical references (p. 16).Mode of access: Internet

Investigation of a 0.6 hub-tip radius-ratio transonic turbine designed for secondary-flow study.

Rohlik, Harold E.
Scibbe, Herbert W.
Wintucky, William T.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.
United States. National Advisory Committee for Aeronautics.

January 1957

"January 9, 1957."Includes bibliographical references (p. 13-14).Mode of access: Internet

Low-speed cascade investigation of loaded leading-edge compressor blades /

Emery, James C.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1956

"January 11, 1956."Includes bibliographical references (p. 11).Mode of access: Internet

Compressor-blade vibration of a J57-P-1 turbojet engine during exploratory operation with inlet-pressure distortions /

Hanson, Morgan P.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"December 23,1955."Includes bibliographical references (p. 11).Mode of access: Internet

Experimental investigation of a transonic axial-flow-compressor rotor with double-circular-arc airfoil blade sections.

Lewis, George W., Jr.
Serovy, G. K. (George K.)
Schwenk, Francis C.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1954

"Declassified October 31, 1958.""April 5, 1954."Cover title.Includes bibliographical references (p. ...

Vibration survey of blades in 10-stage axial-flow compressor

Meyer, Andre J. Jr.
Calvert, Howard F., joint author.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Lewis Flight Propulsion Laboratory.

On front cover: "January 31, 1949."Includes bibliographical references: p. 6.Mode of access: Interne...

Experimental investigation of an axial-flow supersonic compressor having sharp leading-edge blades with an 8-percent mean thickness-chord ratio /

Goldberg, Theodore J.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"February 4, 1955."Includes bibliographical references (p. 12).Mode of access: Internet

Preliminary investigation of hollow-bladed turbines having closed and open blade tips /

Smith, Gordon T.
Hickel, Robert O.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"August 16, 1955."Includes bibliographical references (p. 10).Mode of access: Internet

Performance of external-compression bump inlet at Mach numbers of 1.5 to 2.0 /

Simon, Paul C.
Huff, Ronald G.
Brown, Dennis W.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1957

"April 24, 1957."Includes bibliographical references (p. 9).Mode of access: Internet

Evaluation of a compressor bleed system for rim cooling the turbine wheel of a turbojet engine /

Morse, C. R.
Kemp, R. H.
United States. National Advisory Committee for Aeronautics.

"Declassified February 10, 1959.""March 22, 1954."Cover title.Includes bibliographical references (p...

The performance of conical supersonic scoop inlets on circular fuselages /

Hasel, Lowell E.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"November 17, 1953."Includes bibliographical references (p. 7).Mode of access: Internet

Rotating stall investigation of the 0.72 hub-tip ratio single-stage compressor /

Abstract

Extracted data

Rotating stall investigation of the 0.72 hub-tip ratio single-stage compressor /

Abstract

Extracted data

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