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

Analysis of the dynamic response of a supersonic inlet to flow-field perturbations upstream of the normal shock /

Cole, Gary L.
Willoh, Ross G.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 26-27).Mode of...

Calculation of supersonic stream parameters of a real gas from measurable quantities using FORTRAN IV routines /

Johnson, Robert C. (Robert Clinton), 1924-
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 86-87).Mode of...

A supersonic three-dimensional code for flow over blunt bodies : program documentation and test cases /

Chaussee, D. S.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"February 1980"--Cover.Includes Bibliographical reference.Mode of access: Internet

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

Biringen, Sedat.
McMillan, Oden J.
Langley 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 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

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

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 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...

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...

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

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

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...

Computer program for calculating the flow field of supersonic ejector nozzles /

Anderson, Bernhard H.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 83).Mode of ac...

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

Analysis of the dynamic response of a supersonic inlet to flow-field perturbations upstream of the normal shock /

Cole, Gary L.
Willoh, Ross G.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 26-27).Mode of...

Calculation of supersonic stream parameters of a real gas from measurable quantities using FORTRAN IV routines /

Johnson, Robert C. (Robert Clinton), 1924-
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 86-87).Mode of...

A supersonic three-dimensional code for flow over blunt bodies : program documentation and test cases /

Chaussee, D. S.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"February 1980"--Cover.Includes Bibliographical reference.Mode of access: Internet

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

Biringen, Sedat.
McMillan, Oden J.
Langley 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 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

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

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 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...

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...

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

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

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...

Computer program for calculating the flow field of supersonic ejector nozzles /

Anderson, Bernhard H.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 83).Mode of ac...

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

Analysis of the dynamic response of a supersonic inlet to flow-field perturbations upstream of the normal shock /

Cole, Gary L.
Willoh, Ross G.
Lewis Research Center.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 26-27).Mode of...

Calculation of supersonic stream parameters of a real gas from measurable quantities using FORTRAN IV routines /

Johnson, Robert C. (Robert Clinton), 1924-
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 86-87).Mode of...

A supersonic three-dimensional code for flow over blunt bodies : program documentation and test cases /

Chaussee, D. S.
McMillan, Oden J.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"February 1980"--Cover.Includes Bibliographical reference.Mode of access: Internet

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

Abstract

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

Abstract

Extracted data

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