Pressure distributions and wave drag due to two-dimensional fabrication-type surface roughness on an ogive cylinder at mach numbers of 1.61 and 2.01 /

Effect of fabrication-type surface roughness on transition on ogive-cylinder models at Mach number of 1.61 and 2.01 /

Howard, Paul W.
Czarnecki, K. R.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for two trapezoidal and three delta wings having different surface shapes /

Landrum, Emma Jean.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aerodynamics, aircraft; Aircraft;Stresses and loads.Includes bibliograp...

Induced pressures on cylindrical rods with various nose drags and nose shapes at mach numbers of 17 and 21 /

Witcofski, Robert D.
Henderson, Arthur.
United States. National Aeronautics and Space Administration.

Cover title."May 1962."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibliogra...

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...

Pressure distributions on two-dimensional sharp-leading-edge flat plates with sweep angles of 0 degrees, 30 degrees, and 45 degrees at a mach number of 6 and angles of attack from 0 degrees to 90 degrees / James G. Hondros.

Hondros, James G.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aircraft; Atmospheric entry; Fluid mechanics.Includes bibliographical r...

Experimental pressure distributions over blunt two- and three-dimensional bodies having similar cross sections at a mach number of 4.95 /

Julius, Jerome D.
United States. National Aeronautics and Space Administration.

Cover title."September 1959."Flow, mixed; Flow, supersonic; Bodies, thickness distribution.Includes ...

Effect of shock impingement on the distribution of heat-transfer coefficients on a right circular cylinder at mach numbers of 2.65, 3.51, and 4.44 /

Newlander, Robert A.
United States. National Aeronautics and Space Administration.

Cover title."January 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Fluid ...

Laminar heat-transfer and pressure-distribution studies on a series of reentry nose shapes at a mach number of 19.4 in helium. /

Wagner, Richard D.
Henderson, Arthur, 1922-
Pine, W. Clint.
United States. National Aeronautics and Space Administration.

Cover title."June 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibliogr...

Hypersonic aerodynamic characteristics of minimum-wave-drag bodies having variations in cross-sectional shape /

Spencer, Bernard, 1932-
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."September 1967."Includes bibliographical references (p. 10).Mode of access: Internet

Investigation of effects of roughness, surface cooling, and shock impingement on boundary-layer transition on a two-dimensional wing /

Czarnecki, K. R.
Sevier, John R.
United States. National Aeronautics and Space Administration.

Cover title."June 1960."Flow, laminar; Flow, turbulent; Aerodynamics with heat; Surface conditions,...

Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 /

Cubbison, Robert W.
Ward, James J.
Anderson, Bernhard H.
Lewis Research Center.

Prepared at Lewis Research Center."February 1961."Cover title.Includes bibliographical references (p...

Comparison of experimental and theoretical shock shapes and pressure distributions on flat-faced cylinders at Mach 10.5 /

Inouye, Mamoru.
Sinclair, A. Richard.
Marvin, Joseph G.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."February 1968."Includes bibliographical references (p. 8).Mode of access: Internet

Numerical solutions for supersonic flow of an ideal gas around blunt two-dimensional bodies /

Fuller, Franklyn B.
United States. National Aeronautics and Space Administration.

Cover title."July 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Fluid mec...

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...

Effect of fabrication-type surface roughness on transition on ogive-cylinder models at Mach number of 1.61 and 2.01 /

Howard, Paul W.
Czarnecki, K. R.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for two trapezoidal and three delta wings having different surface shapes /

Landrum, Emma Jean.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aerodynamics, aircraft; Aircraft;Stresses and loads.Includes bibliograp...

Induced pressures on cylindrical rods with various nose drags and nose shapes at mach numbers of 17 and 21 /

Witcofski, Robert D.
Henderson, Arthur.
United States. National Aeronautics and Space Administration.

Cover title."May 1962."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibliogra...

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...

Pressure distributions on two-dimensional sharp-leading-edge flat plates with sweep angles of 0 degrees, 30 degrees, and 45 degrees at a mach number of 6 and angles of attack from 0 degrees to 90 degrees / James G. Hondros.

Hondros, James G.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aircraft; Atmospheric entry; Fluid mechanics.Includes bibliographical r...

Experimental pressure distributions over blunt two- and three-dimensional bodies having similar cross sections at a mach number of 4.95 /

Julius, Jerome D.
United States. National Aeronautics and Space Administration.

Cover title."September 1959."Flow, mixed; Flow, supersonic; Bodies, thickness distribution.Includes ...

Effect of shock impingement on the distribution of heat-transfer coefficients on a right circular cylinder at mach numbers of 2.65, 3.51, and 4.44 /

Newlander, Robert A.
United States. National Aeronautics and Space Administration.

Cover title."January 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Fluid ...

Laminar heat-transfer and pressure-distribution studies on a series of reentry nose shapes at a mach number of 19.4 in helium. /

Wagner, Richard D.
Henderson, Arthur, 1922-
Pine, W. Clint.
United States. National Aeronautics and Space Administration.

Cover title."June 1961."Aerodynamics, missiles and space vehicles; Fluid mechanics.Includes bibliogr...

Hypersonic aerodynamic characteristics of minimum-wave-drag bodies having variations in cross-sectional shape /

Spencer, Bernard, 1932-
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1967

Cover title."September 1967."Includes bibliographical references (p. 10).Mode of access: Internet

Investigation of effects of roughness, surface cooling, and shock impingement on boundary-layer transition on a two-dimensional wing /

Czarnecki, K. R.
Sevier, John R.
United States. National Aeronautics and Space Administration.

Cover title."June 1960."Flow, laminar; Flow, turbulent; Aerodynamics with heat; Surface conditions,...

Surface pressure distributions with a sonic jet normal to adjacent flat surfaces at Mach 2.92 to 6.4 /

Cubbison, Robert W.
Ward, James J.
Anderson, Bernhard H.
Lewis Research Center.

Prepared at Lewis Research Center."February 1961."Cover title.Includes bibliographical references (p...

Comparison of experimental and theoretical shock shapes and pressure distributions on flat-faced cylinders at Mach 10.5 /

Inouye, Mamoru.
Sinclair, A. Richard.
Marvin, Joseph G.
Ames Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."February 1968."Includes bibliographical references (p. 8).Mode of access: Internet

Numerical solutions for supersonic flow of an ideal gas around blunt two-dimensional bodies /

Fuller, Franklyn B.
United States. National Aeronautics and Space Administration.

Cover title."July 1961."Aerodynamics, aircraft; Aerodynamics, missiles and space vehicles; Fluid mec...

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...

Effect of fabrication-type surface roughness on transition on ogive-cylinder models at Mach number of 1.61 and 2.01 /

Howard, Paul W.
Czarnecki, K. R.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

Pressure distributions on blunt-delta wings at angles of attack up to 90 degrees and Mach number of 6.85 /

Bernot, Peter T.
United States. National Aeronautics and Space Administration.

Cover title."July 1963."Includes bibliographical references.Mode of access: Internet

A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for two trapezoidal and three delta wings having different surface shapes /

Landrum, Emma Jean.
United States. National Aeronautics and Space Administration.

Cover title."September 1962."Aerodynamics, aircraft; Aircraft;Stresses and loads.Includes bibliograp...

Pressure distributions and wave drag due to two-dimensional fabrication-type surface roughness on an ogive cylinder at mach numbers of 1.61 and 2.01 /

Abstract

Extracted data

Pressure distributions and wave drag due to two-dimensional fabrication-type surface roughness on an ogive cylinder at mach numbers of 1.61 and 2.01 /

Abstract

Extracted data

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