Numerical analysis of the scramjet-inlet flow field by using two-dimensional Navier-Stokes equations /

Calculation of two-dimensional inlet flow fields by an implicit method including viscous effects : User's manual /

Biringen, Sedat.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

STAR category 02."May 1981"--Cover.Includes bibliographical references.Mode of access: Internet

Development and validation of a combined rotor-fuselage induced flow-field computational method /

Freeman, Carl E.
Army Research and Technology Laboratories (U.S.). Structures Laboratory.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

Subject Category 02."Structures Laboratory, AVRADCOM Research and Technology Laboratories.""June 198...

Flow field analysis of aircraft configurations using a numerical solution to the three-dimensional unified supersonic/hypersonic small disturbance equations /

Gunness, R. C.
Dsylva, E.
Knight, C. J.
Langley Research Center.
Boeing Company.

January 1972

"February 1972."Cover title.Performed by the Boeing Company, Seattle, Wash., for Langley Research C...

Analysis of the scramjet inlet flow field using two-dimensional Navier-Stokes equations /

Kumar, Ajay.
Tiwari, S. N.
Old Dominion University. Research Foundation.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1982

"June 1982"--Cover."Old Dominion University Research Foundation"--Tech. rep. p.Includes bibliographi...

Some observations on a new numerical method for solving the Navier-Stokes equations /

Kumar, Ajay.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject Category 02."November 1981"--Cover."Langley Research Center."Includes bibliographical refere...

Assessment of turbulence models for scramjet flowfields /

Sindir, M. M.
Harsha, P. T.
Science Applications, inc. Combustion Science and Advanced Technology Dept.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

"November 1982"--Cover."Science Applications, Inc., Combustion Science and Advanced Technology Depar...

Calculation of two-dimensional inlet flow fields in a supersonic free stream : program documentation and test cases /

Biringen, Sedat.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"March 1980"--Cover.Includes bibliographical references.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 ...

Development of a three-dimensional supersonic inlet flow analysis /

Buggeln, R. C.
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"January 1980"--Cover.Includes bibliographical references.Mode of access: Internet

Theoretical and experimental flow fields for a supersonic cruise fighter forebody /

Yaros, Steven F.
Langley Research Center.

January 1985

Prepared at Langley Research Center."November 1984"--Cover.Includes bibliographical references (p. 7...

Experimental and analytical study of an inlet forebody for an airframe-integrated scramjet concept /

Andrews, Earl H.
Pinckney, S. Z. (Shimer Zane), 1934-
Agnone, Anthony M.
Langley Research Center.

January 1975

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

Investigation of a supersonic cruise fighter model flow field /

Reubush, David E.
Bare, E. Ann.
Langley Research Center.

January 1985

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

Calculation of two-dimensional inlet flow fields by an implicit method including viscous effects - program documentation and test case /

Biringen, Sedat.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Chiefly tables."June 1981"--Cover.Includes bibliographical references.Mode of access: Internet

Viscous computations of cold air/air flow around scramjet nozzle afterbody /

Baysal, Oktay.
Englelund, Walter C.
Old Dominion University. Dept. of Mechanical Engineering and Mechanics.
Langley Research Center.

January 1991

Prepared at the Mechanical Engineering & Mechanics Dept., Old Dominion University, for Langley Resea...

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...

Calculation of two-dimensional inlet flow fields by an implicit method including viscous effects : User's manual /

Biringen, Sedat.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

STAR category 02."May 1981"--Cover.Includes bibliographical references.Mode of access: Internet

Development and validation of a combined rotor-fuselage induced flow-field computational method /

Freeman, Carl E.
Army Research and Technology Laboratories (U.S.). Structures Laboratory.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

Subject Category 02."Structures Laboratory, AVRADCOM Research and Technology Laboratories.""June 198...

Flow field analysis of aircraft configurations using a numerical solution to the three-dimensional unified supersonic/hypersonic small disturbance equations /

Gunness, R. C.
Dsylva, E.
Knight, C. J.
Langley Research Center.
Boeing Company.

January 1972

"February 1972."Cover title.Performed by the Boeing Company, Seattle, Wash., for Langley Research C...

Analysis of the scramjet inlet flow field using two-dimensional Navier-Stokes equations /

Kumar, Ajay.
Tiwari, S. N.
Old Dominion University. Research Foundation.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1982

"June 1982"--Cover."Old Dominion University Research Foundation"--Tech. rep. p.Includes bibliographi...

Some observations on a new numerical method for solving the Navier-Stokes equations /

Kumar, Ajay.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Subject Category 02."November 1981"--Cover."Langley Research Center."Includes bibliographical refere...

Assessment of turbulence models for scramjet flowfields /

Sindir, M. M.
Harsha, P. T.
Science Applications, inc. Combustion Science and Advanced Technology Dept.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

"November 1982"--Cover."Science Applications, Inc., Combustion Science and Advanced Technology Depar...

Calculation of two-dimensional inlet flow fields in a supersonic free stream : program documentation and test cases /

Biringen, Sedat.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"March 1980"--Cover.Includes bibliographical references.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 ...

Development of a three-dimensional supersonic inlet flow analysis /

Buggeln, R. C.
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"January 1980"--Cover.Includes bibliographical references.Mode of access: Internet

Theoretical and experimental flow fields for a supersonic cruise fighter forebody /

Yaros, Steven F.
Langley Research Center.

January 1985

Prepared at Langley Research Center."November 1984"--Cover.Includes bibliographical references (p. 7...

Experimental and analytical study of an inlet forebody for an airframe-integrated scramjet concept /

Andrews, Earl H.
Pinckney, S. Z. (Shimer Zane), 1934-
Agnone, Anthony M.
Langley Research Center.

January 1975

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

Investigation of a supersonic cruise fighter model flow field /

Reubush, David E.
Bare, E. Ann.
Langley Research Center.

January 1985

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

Calculation of two-dimensional inlet flow fields by an implicit method including viscous effects - program documentation and test case /

Biringen, Sedat.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

Chiefly tables."June 1981"--Cover.Includes bibliographical references.Mode of access: Internet

Viscous computations of cold air/air flow around scramjet nozzle afterbody /

Baysal, Oktay.
Englelund, Walter C.
Old Dominion University. Dept. of Mechanical Engineering and Mechanics.
Langley Research Center.

January 1991

Prepared at the Mechanical Engineering & Mechanics Dept., Old Dominion University, for Langley Resea...

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...

Calculation of two-dimensional inlet flow fields by an implicit method including viscous effects : User's manual /

Biringen, Sedat.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

STAR category 02."May 1981"--Cover.Includes bibliographical references.Mode of access: Internet

Development and validation of a combined rotor-fuselage induced flow-field computational method /

Freeman, Carl E.
Army Research and Technology Laboratories (U.S.). Structures Laboratory.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

Subject Category 02."Structures Laboratory, AVRADCOM Research and Technology Laboratories.""June 198...

Flow field analysis of aircraft configurations using a numerical solution to the three-dimensional unified supersonic/hypersonic small disturbance equations /

Gunness, R. C.
Dsylva, E.
Knight, C. J.
Langley Research Center.
Boeing Company.

January 1972

"February 1972."Cover title.Performed by the Boeing Company, Seattle, Wash., for Langley Research C...

Numerical analysis of the scramjet-inlet flow field by using two-dimensional Navier-Stokes equations /

Abstract

Extracted data

Numerical analysis of the scramjet-inlet flow field by using two-dimensional Navier-Stokes equations /

Abstract

Extracted data

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