The effects of boundary-layer removal through throat slots on the internal performance of a side inlet at Mach numbers of 2.0 and 2.3 /

Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71 /

Morris, W. Douglas.
Couch, Lana M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 12).Mode of access: Internet

Effects of leading-edge bluntness and ramp deflection angle on laminar boundary-layer separation in hypersonic flow /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.

Prepared at Langley Research Center."February 1966"--Cover.Includes bibliographical references (p. 2...

Effects of mach number, leading edge bluntness and sweep on boundary-layer transition on a flat plate /

Jillie, Don W.
Hopkins, Edward J.
United States. National Aeronautics and Space Administration.

Cover title."September 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bib...

Effect of centerbody boundary-layer removal near the throat of three conical nose inlets at mach 1.6 to 2.0 /

Kremzier, Emil J.
Wise, George A.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"November 15, 1955."Includes bibliographical references (p. 7-8).Mode of access: Internet

An experimental investigation at mach numbers from 2.1 to 3.0 of circular internal-compression inlets having translatable centerbodies and provisions for boundary-layer removal /

Watson, Earl C.
United States. National Aeronautics and Space Administration.

"January 1960."Cover title.Includes bibliographical references (p. 11).Mode of access: Internet

A comparison of the performance of four side-mounted inlets over a Mach number range of 0.88 to 2.2 and angles of attack to 14° /

Presley, Leroy L.
Peterson, William P.
Ames Research Center.

January 1960

"January 1960."Caption title.Includes bibliographical references (p. 14-15).Mode of access: Internet

The effect of the inlet mach number and inlet-boundary-layer thickness on the performance of a 23©� conical-diffuser-tail-pipe combination /

Persh, Jerome.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1950

"March 21, 1950."Includes bibliographical references (p. 21).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

Some considerations concerning inlets and ducted bodies at Mach numbers from 0.8 to 2.0 /

Sears, Richard I.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"November 24, 1953."Includes bibliographical references (p. 10-11).Mode of access: Internet

Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 /

Bowditch, David N.
Tabata, William K.
Anderson, Bernhard H.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Performance and boundary-layer evaluation of a sonic inlet /

Schmidt, James F.
Ruggeri, Robert S., joint author.
Lewis Research Center.

January 1976

Cover title.Includes bibliographical references (p. 25).Mode of access: Internet

Some effects of leading-edge sweep on boundary-layer transition at supersonic speeds /

Chapman, Gary T.
United States. National Aeronautics and Space Administration.

Cover title."September 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Flui...

Transonic performance of a Mach 2.65 auxiliary flow axisymmetric inlet /

Santman, Don M.
United States. National Aeronautics and Space Administration.
Ames Research Center.
Ellco Engineering, Inc.

January 1976

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

Aerodynamic and acoustic performance of high Mach number inlets /

Lumsdaine, Edward.
United States. National Aeronautics and Space Administration.

January 1977

Issued Aug. 1977.Includes bibliographical references (p. 12-15).Mode of access: Internet

Throat stability-bypass systems to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction /

Mitchell, Glenn A.
Shaw, Robert J. (Robert Joseph), 1946-
Sanders, Bobby W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 18).Mode of ac...

Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71 /

Morris, W. Douglas.
Couch, Lana M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 12).Mode of access: Internet

Effects of leading-edge bluntness and ramp deflection angle on laminar boundary-layer separation in hypersonic flow /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.

Prepared at Langley Research Center."February 1966"--Cover.Includes bibliographical references (p. 2...

Effects of mach number, leading edge bluntness and sweep on boundary-layer transition on a flat plate /

Jillie, Don W.
Hopkins, Edward J.
United States. National Aeronautics and Space Administration.

Cover title."September 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bib...

Effect of centerbody boundary-layer removal near the throat of three conical nose inlets at mach 1.6 to 2.0 /

Kremzier, Emil J.
Wise, George A.
Lewis Flight Propulsion Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1955

"November 15, 1955."Includes bibliographical references (p. 7-8).Mode of access: Internet

An experimental investigation at mach numbers from 2.1 to 3.0 of circular internal-compression inlets having translatable centerbodies and provisions for boundary-layer removal /

Watson, Earl C.
United States. National Aeronautics and Space Administration.

"January 1960."Cover title.Includes bibliographical references (p. 11).Mode of access: Internet

A comparison of the performance of four side-mounted inlets over a Mach number range of 0.88 to 2.2 and angles of attack to 14° /

Presley, Leroy L.
Peterson, William P.
Ames Research Center.

January 1960

"January 1960."Caption title.Includes bibliographical references (p. 14-15).Mode of access: Internet

The effect of the inlet mach number and inlet-boundary-layer thickness on the performance of a 23©� conical-diffuser-tail-pipe combination /

Persh, Jerome.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1950

"March 21, 1950."Includes bibliographical references (p. 21).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

Some considerations concerning inlets and ducted bodies at Mach numbers from 0.8 to 2.0 /

Sears, Richard I.
Langley Aeronautical Laboratory.
United States. National Adviosry Committee for Aeronautics. NACA research memorandum.

January 1953

"November 24, 1953."Includes bibliographical references (p. 10-11).Mode of access: Internet

Performance of a turbojet engine in combination with an external-internal-compression inlet to mach 2.88 /

Bowditch, David N.
Tabata, William K.
Anderson, Bernhard H.
United States. National Aeronautics and Space Administration.

"July 1960."Cover title.Includes bibliographical references (p. 10-11).Mode of access: Internet

Performance and boundary-layer evaluation of a sonic inlet /

Schmidt, James F.
Ruggeri, Robert S., joint author.
Lewis Research Center.

January 1976

Cover title.Includes bibliographical references (p. 25).Mode of access: Internet

Some effects of leading-edge sweep on boundary-layer transition at supersonic speeds /

Chapman, Gary T.
United States. National Aeronautics and Space Administration.

Cover title."September 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Flui...

Transonic performance of a Mach 2.65 auxiliary flow axisymmetric inlet /

Santman, Don M.
United States. National Aeronautics and Space Administration.
Ames Research Center.
Ellco Engineering, Inc.

January 1976

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

Aerodynamic and acoustic performance of high Mach number inlets /

Lumsdaine, Edward.
United States. National Aeronautics and Space Administration.

January 1977

Issued Aug. 1977.Includes bibliographical references (p. 12-15).Mode of access: Internet

Throat stability-bypass systems to increase the stable airflow range of a Mach 2.5 inlet with 60-percent internal contraction /

Mitchell, Glenn A.
Shaw, Robert J. (Robert Joseph), 1946-
Sanders, Bobby W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 18).Mode of ac...

Experimental pressure distributions on a blunt lifting-entry body at Mach 3.71 /

Morris, W. Douglas.
Couch, Lana M.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."April 1968."Includes bibliographical references (p. 12).Mode of access: Internet

Effects of leading-edge bluntness and ramp deflection angle on laminar boundary-layer separation in hypersonic flow /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.

Prepared at Langley Research Center."February 1966"--Cover.Includes bibliographical references (p. 2...

Effects of mach number, leading edge bluntness and sweep on boundary-layer transition on a flat plate /

Jillie, Don W.
Hopkins, Edward J.
United States. National Aeronautics and Space Administration.

Cover title."September 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bib...

The effects of boundary-layer removal through throat slots on the internal performance of a side inlet at Mach numbers of 2.0 and 2.3 /

Abstract

Extracted data

The effects of boundary-layer removal through throat slots on the internal performance of a side inlet at Mach numbers of 2.0 and 2.3 /

Abstract

Extracted data

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