Boundary-layer transition and displacement-thickness effects on zero-lift drag of a series of power-law bodies at Mach 6 /

The effect of thrust minus base drag of exchanging base area for nozzle expansion in supersonic nozzles at transonic mach numbers /

Slocumb, Travis H.
Andrews, Earl H.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Aircraft...

Influence of the body flow field on the zero-lift wave drag of wing-body combinations modified in accordance with the transonic area rule /

Page, William A.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

On front cover: "February 7, 1956."Includes bibliographical references: p. 19-20.Mode of access: Int...

Flight-measured laminar boundary layer transition phenomena including stability theory analysis /

Obara, Clifford J.
Holmes, Bruce J.
Langley Research Center.

January 1985

Prepared at Langley Research Center."April 1985"--Cover.Includes bibliographical references (p. 8).M...

Longitudinal aerodynamic performance of a series of power-law and minimum-wave-drag bodies at Mach 6 and several Reynolds numbers /

Ashby, George C.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Experimental and numerical investigation of boundary-layer development and transition on the walls of a Mach 5 nozzle /

Harvey, William D., 1934-
Harris, Julius E.
Cary, Aubrey M.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 23-25).Mode ...

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...

Boundary-layer transition and displacement thickness effects on zero-lift drag of a series of power-law bodies at Mach 6

Ashby, G. C., Jr.
Harris, J. E.

September 1974

Wave and skin-friction drag have been numerically calculated for a series of power-law bodies at a M...

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...

Sweep effect on the drag of rows of perpendicular circular cylinders in a laminar boundary layer at supersonic free-stream velocities /

Lamb, Milton.
Stallings, Robert L.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Weak incident shock interactions with Mach 8 laminar boundary layers /

Kaufman, Louis G.
Johnson, Charles B.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 21-23).Mode ...

Boundary-layer velocity profiles downstream of three-dimensional transition trips on a flat plate at Mach 3 and 4 /

Peterson, John B.
United States. National Aeronautics and Space Administration.
Langley Research Center.

Boundary layer velocity profiles downstream of three dimensional transition trips on flat plates at ...

Boundary-layer transition on a group of blunt nose shapes at a mach number of 2.20 /

Jackson, Mary W.
Czatnecki, K. R.
United States. National Aeronautics and Space Administration.

Cover title."July 1961."Major NASA subject terms: Aerodynamics, aircraft; Aerodynamics, missiles and...

Effects of Mach number on pitot-probe displacment in a turbulent boundary layer /

Allen, Jerry M.
Langley Research Center.

January 1974

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

The effect of acceleration versus displacement methods on steady-state boundary forces /

McGhee, David S.
George C. Marshall Space Flight Center.

January 1992

Prepared at George C. Marshall Space Flight Center.Includes bibliographical references (p. 16).Mode ...

Hypersonic aerodynamic characteristics of a family of power-law, wing-body configuratioons /

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

January 1973

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

The effect of thrust minus base drag of exchanging base area for nozzle expansion in supersonic nozzles at transonic mach numbers /

Slocumb, Travis H.
Andrews, Earl H.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Aircraft...

Influence of the body flow field on the zero-lift wave drag of wing-body combinations modified in accordance with the transonic area rule /

Page, William A.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

On front cover: "February 7, 1956."Includes bibliographical references: p. 19-20.Mode of access: Int...

Flight-measured laminar boundary layer transition phenomena including stability theory analysis /

Obara, Clifford J.
Holmes, Bruce J.
Langley Research Center.

January 1985

Prepared at Langley Research Center."April 1985"--Cover.Includes bibliographical references (p. 8).M...

Longitudinal aerodynamic performance of a series of power-law and minimum-wave-drag bodies at Mach 6 and several Reynolds numbers /

Ashby, George C.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Experimental and numerical investigation of boundary-layer development and transition on the walls of a Mach 5 nozzle /

Harvey, William D., 1934-
Harris, Julius E.
Cary, Aubrey M.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 23-25).Mode ...

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...

Boundary-layer transition and displacement thickness effects on zero-lift drag of a series of power-law bodies at Mach 6

Ashby, G. C., Jr.
Harris, J. E.

September 1974

Wave and skin-friction drag have been numerically calculated for a series of power-law bodies at a M...

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...

Sweep effect on the drag of rows of perpendicular circular cylinders in a laminar boundary layer at supersonic free-stream velocities /

Lamb, Milton.
Stallings, Robert L.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 8).Mode of a...

Weak incident shock interactions with Mach 8 laminar boundary layers /

Kaufman, Louis G.
Johnson, Charles B.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 21-23).Mode ...

Boundary-layer velocity profiles downstream of three-dimensional transition trips on a flat plate at Mach 3 and 4 /

Peterson, John B.
United States. National Aeronautics and Space Administration.
Langley Research Center.

Boundary layer velocity profiles downstream of three dimensional transition trips on flat plates at ...

Boundary-layer transition on a group of blunt nose shapes at a mach number of 2.20 /

Jackson, Mary W.
Czatnecki, K. R.
United States. National Aeronautics and Space Administration.

Cover title."July 1961."Major NASA subject terms: Aerodynamics, aircraft; Aerodynamics, missiles and...

Effects of Mach number on pitot-probe displacment in a turbulent boundary layer /

Allen, Jerry M.
Langley Research Center.

January 1974

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

The effect of acceleration versus displacement methods on steady-state boundary forces /

McGhee, David S.
George C. Marshall Space Flight Center.

January 1992

Prepared at George C. Marshall Space Flight Center.Includes bibliographical references (p. 16).Mode ...

Hypersonic aerodynamic characteristics of a family of power-law, wing-body configuratioons /

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

January 1973

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

The effect of thrust minus base drag of exchanging base area for nozzle expansion in supersonic nozzles at transonic mach numbers /

Slocumb, Travis H.
Andrews, Earl H.
United States. National Aeronautics and Space Administration.

Cover title."April 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Aircraft...

Influence of the body flow field on the zero-lift wave drag of wing-body combinations modified in accordance with the transonic area rule /

Page, William A.
United States. National Advisory Committee for Aeronautics. NACA research memorandum.
Ames Research Center.

On front cover: "February 7, 1956."Includes bibliographical references: p. 19-20.Mode of access: Int...

Flight-measured laminar boundary layer transition phenomena including stability theory analysis /

Obara, Clifford J.
Holmes, Bruce J.
Langley Research Center.

January 1985

Prepared at Langley Research Center."April 1985"--Cover.Includes bibliographical references (p. 8).M...

Boundary-layer transition and displacement-thickness effects on zero-lift drag of a series of power-law bodies at Mach 6 /

Abstract

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Boundary-layer transition and displacement-thickness effects on zero-lift drag of a series of power-law bodies at Mach 6 /

Abstract

Extracted data

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