Calculation of two-dimensional inlet flow fields in a supersonic free strem by an implicit marching code with nonorthogonal mesh generation : user's manual /

Inverse-method and method-of-characteristics flow-field programs /

Moreno, J. B., author.
U.S. Atomic Energy Commission.
Sandia Corporation.

Two flow-field computer codes are described. The codes were developed to compute the flow about blun...

Computation of transonic potential flow about three-dimensional inlets, ducts, and bodies /

Reyhner, Theodore A.
Boeing Commercial Airplane Company.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

Subject Category 02."March 1982"--Cover.Includes bibliographical references.Mode of access: Internet

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

Mcmillan, O. J.
Biringen, S.

May 1981

Inlet flow fields for airbreathing missiles are calculated by the adaptation of a two dimensional co...

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

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

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

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

Biringen, S. H.
Mcmillan, O. J.

March 1980

The use of a computer code for the calculation of two dimensional inlet flow fields in a supersonic ...

An implicit method for the calculation of inlet flow fields /

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

January 1981

"June 1981"--Cover."Nielsen Engineering & Research, Inc."Includes bibliographical references.Mode of...

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

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

January 1981

Subject Category 07."Langley Research Center.""December 1981"--Cover.Includes bibliographical refere...

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

Mcmillan, O. J.
Biringen, S.

June 1981

The source listing of a computer code for calculating the flow fields in a supersonic free stream is...

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...

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

Development of a computer code for calculating the steady super/hypersonic inviscid flow around real configurations : volume I-computational technique /

Marconi, Frank.
Yaeger, Larry, joint author.
Salas, Manuel, joint author.
United States. National Aeronautics and Space Administration.
Grumman Aerospace Corporation.

January 1976

Cover title.Includes bibliographical references (p. 87-88).Mode of access: Internet

Inlet spillage drag tests and numerical flow-field analysis at subsonic and transonic speeds of a 1/8-scale, two-dimensional, external-compression, variable-geometry supersonic inlet configuration /

Hawkins, J. E.
Turner, R. L. (Ralph Lilley), Sir, 1888-1983, joint author.
Kirkland, F. P., joint author.
Ames Research Center.
General Dynamics Corporation. Convair Aerospace Division.
United States. National Aeronautics and Space Administration.

January 1976

Cover title.Includes bibliographical references (p. 46).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

Inverse-method and method-of-characteristics flow-field programs /

Moreno, J. B., author.
U.S. Atomic Energy Commission.
Sandia Corporation.

Two flow-field computer codes are described. The codes were developed to compute the flow about blun...

Computation of transonic potential flow about three-dimensional inlets, ducts, and bodies /

Reyhner, Theodore A.
Boeing Commercial Airplane Company.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

Subject Category 02."March 1982"--Cover.Includes bibliographical references.Mode of access: Internet

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

Mcmillan, O. J.
Biringen, S.

May 1981

Inlet flow fields for airbreathing missiles are calculated by the adaptation of a two dimensional co...

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

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

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

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

Biringen, S. H.
Mcmillan, O. J.

March 1980

The use of a computer code for the calculation of two dimensional inlet flow fields in a supersonic ...

An implicit method for the calculation of inlet flow fields /

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

January 1981

"June 1981"--Cover."Nielsen Engineering & Research, Inc."Includes bibliographical references.Mode of...

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

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

January 1981

Subject Category 07."Langley Research Center.""December 1981"--Cover.Includes bibliographical refere...

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

Mcmillan, O. J.
Biringen, S.

June 1981

The source listing of a computer code for calculating the flow fields in a supersonic free stream is...

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...

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

Development of a computer code for calculating the steady super/hypersonic inviscid flow around real configurations : volume I-computational technique /

Marconi, Frank.
Yaeger, Larry, joint author.
Salas, Manuel, joint author.
United States. National Aeronautics and Space Administration.
Grumman Aerospace Corporation.

January 1976

Cover title.Includes bibliographical references (p. 87-88).Mode of access: Internet

Inlet spillage drag tests and numerical flow-field analysis at subsonic and transonic speeds of a 1/8-scale, two-dimensional, external-compression, variable-geometry supersonic inlet configuration /

Hawkins, J. E.
Turner, R. L. (Ralph Lilley), Sir, 1888-1983, joint author.
Kirkland, F. P., joint author.
Ames Research Center.
General Dynamics Corporation. Convair Aerospace Division.
United States. National Aeronautics and Space Administration.

January 1976

Cover title.Includes bibliographical references (p. 46).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

Inverse-method and method-of-characteristics flow-field programs /

Moreno, J. B., author.
U.S. Atomic Energy Commission.
Sandia Corporation.

Two flow-field computer codes are described. The codes were developed to compute the flow about blun...

Computation of transonic potential flow about three-dimensional inlets, ducts, and bodies /

Reyhner, Theodore A.
Boeing Commercial Airplane Company.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1982

Subject Category 02."March 1982"--Cover.Includes bibliographical references.Mode of access: Internet

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

Mcmillan, O. J.
Biringen, S.

May 1981

Inlet flow fields for airbreathing missiles are calculated by the adaptation of a two dimensional co...

Calculation of two-dimensional inlet flow fields in a supersonic free strem by an implicit marching code with nonorthogonal mesh generation : user's manual /

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Calculation of two-dimensional inlet flow fields in a supersonic free strem by an implicit marching code with nonorthogonal mesh generation : user's manual /

Abstract

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