A rapid numerical solution to subsonic flow over planar and axisymmetric profiles at an angle of attack of 0 ̊/

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).Mode of access: Internet

A short static-pressure probe design for supersonic flow /

Pinckney, S. Z. (Shimer Zane), 1934-
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode ...

A method for determining surface pressures on blunt bodies of revolution at small angles of attack in supersonic flow /

Jackson, Charlie M.
Smith, Rudeen S.
Sawyer, Wallace C.
United States. National Aeronautics and Space Administration.

Cover title."November 1968."Includes bibliographical references.Mode of access: Internet

Calculation of axisymmetric supersonic flow past blunt bodies with sonic corners : including a program description and listing /

South, Jerry C. (Jerry Curtis), 1935-
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."May 1968."Includes bibliographical references (p. 36-37).Mode of access: Internet

Numerical solutions of the Navier-Stokes equations for the supersonic laminar flow over a two-dimensional compression corner /

Carter, James E. (James Edward), 1944-
Langley Research Center.

January 1972

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 76-79).Mode ...

Steady subsonic flow around finite-thickness wings /

Kuo, Ching-Chiang.
Morino, L.
Langley Research Center.
Boston University. Dept. of Aerospace Engineering.

"Prepared by Boston University, [Dept. of Aerospace Engineering] ... for Langley Research Center.""N...

Numerical methods for the design and analysis of wings at supersonic speeds /

Carlson, Harry W.
Miller, David S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 29-30).Mode ...

Efficient solutions to the Euler equations for supersonic flow with embedded subsonic regions /

Walters, Robert W.
Dwoyer, Douglas L.
Langley Research Center.

January 1987

Prepared at Langley Research Center."January 1987"--Cover.Includes bibliographical references (p. 9)...

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...

A study of methods which predict supersonic flow fields from body geometry, distance, and Mach number /

Mack, Robert J.
Langley Research Center.

January 1973

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 13-14).Mode ...

Application of a numerically generated orthogonal coordinate system to the solution of inviscid axisymmetric supersonic flow over blunt bodies /

Hamilton, H. Harris.
Graves, Randolph A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

Subject Category 02."March 1980"--Cover."Langley Research Center."Includes bibliographical reference...

Subsonic wind-tunnel investigation of a twin-engine attack airplane model having nonmetric powered nacelles /

Lockwood, Vernard E.
Matarazzo, Aniello.
Langley Research Center.

January 1974

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

Subsonic annular wing theory with application to flow about nacelles /

Mann, Michael J.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 90-91).Mode ...

A parametric study of effect of forebody shape on flow angularity at Mach 8 /

Johnson, Charles B.
Marcum, Don C.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode ...

A rapid numerical solution to subsonic flow over planar and axisymmetric profiles at an angle of attack of 0 deg

Mascitti, V. R.

March 1974

A numerical solution is presented for the incompressible flow over thin planar and axisymmetric prof...

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).Mode of access: Internet

A short static-pressure probe design for supersonic flow /

Pinckney, S. Z. (Shimer Zane), 1934-
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode ...

A method for determining surface pressures on blunt bodies of revolution at small angles of attack in supersonic flow /

Jackson, Charlie M.
Smith, Rudeen S.
Sawyer, Wallace C.
United States. National Aeronautics and Space Administration.

Cover title."November 1968."Includes bibliographical references.Mode of access: Internet

Calculation of axisymmetric supersonic flow past blunt bodies with sonic corners : including a program description and listing /

South, Jerry C. (Jerry Curtis), 1935-
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1968

Cover title."May 1968."Includes bibliographical references (p. 36-37).Mode of access: Internet

Numerical solutions of the Navier-Stokes equations for the supersonic laminar flow over a two-dimensional compression corner /

Carter, James E. (James Edward), 1944-
Langley Research Center.

January 1972

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 76-79).Mode ...

Steady subsonic flow around finite-thickness wings /

Kuo, Ching-Chiang.
Morino, L.
Langley Research Center.
Boston University. Dept. of Aerospace Engineering.

"Prepared by Boston University, [Dept. of Aerospace Engineering] ... for Langley Research Center.""N...

Numerical methods for the design and analysis of wings at supersonic speeds /

Carlson, Harry W.
Miller, David S.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 29-30).Mode ...

Efficient solutions to the Euler equations for supersonic flow with embedded subsonic regions /

Walters, Robert W.
Dwoyer, Douglas L.
Langley Research Center.

January 1987

Prepared at Langley Research Center."January 1987"--Cover.Includes bibliographical references (p. 9)...

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...

A study of methods which predict supersonic flow fields from body geometry, distance, and Mach number /

Mack, Robert J.
Langley Research Center.

January 1973

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 13-14).Mode ...

Application of a numerically generated orthogonal coordinate system to the solution of inviscid axisymmetric supersonic flow over blunt bodies /

Hamilton, H. Harris.
Graves, Randolph A.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

Subject Category 02."March 1980"--Cover."Langley Research Center."Includes bibliographical reference...

Subsonic wind-tunnel investigation of a twin-engine attack airplane model having nonmetric powered nacelles /

Lockwood, Vernard E.
Matarazzo, Aniello.
Langley Research Center.

January 1974

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

Subsonic annular wing theory with application to flow about nacelles /

Mann, Michael J.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 90-91).Mode ...

A parametric study of effect of forebody shape on flow angularity at Mach 8 /

Johnson, Charles B.
Marcum, Don C.
Langley Research Center.

January 1974

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode ...

A rapid numerical solution to subsonic flow over planar and axisymmetric profiles at an angle of attack of 0 deg

Mascitti, V. R.

March 1974

A numerical solution is presented for the incompressible flow over thin planar and axisymmetric prof...

Pressure distributions on a 1- by 3-meter semispan wing at sweep angles from 0 ̊to 40 ̊in subsonic flow /

Yip, Long P.
Shubert, l Gary L, joint author.
United States. National Aeronautics and Space Administration.

January 1976

Issued Dec. 1976.Includes bibliographical references (p. 9-10).Mode of access: Internet

A short static-pressure probe design for supersonic flow /

Pinckney, S. Z. (Shimer Zane), 1934-
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode ...

A method for determining surface pressures on blunt bodies of revolution at small angles of attack in supersonic flow /

Jackson, Charlie M.
Smith, Rudeen S.
Sawyer, Wallace C.
United States. National Aeronautics and Space Administration.

Cover title."November 1968."Includes bibliographical references.Mode of access: Internet

A rapid numerical solution to subsonic flow over planar and axisymmetric profiles at an angle of attack of 0 ̊/

Abstract

Extracted data

A rapid numerical solution to subsonic flow over planar and axisymmetric profiles at an angle of attack of 0 ̊/

Abstract

Extracted data

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