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

An approximate method for calculating three-dimensional inviscid hypersonic flow fields /

Riley, Christopher J. (Christopher Joseph), 1964-
DeJarnette, Fred R.
Langley Research Center.

January 1990

Prepared at Langley Research Center.Bibliography: p. 12.Mode of access: Internet

An improved supersonic, three-dimensional, external, inviscid flow field code /

Marconi, Frank.
Koch, Frank, 1931- joint author.
Grumman Aerospace Corporation.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

March 1979.Prepared for Langley Research Center under contract NAS1-14162.Includes bibliographical r...

Some problems of the calculation of three-dimensional boundary-layer flows on general configurations /

Cebeci, Tuncer.
Langley Research Center.
Douglas Aircraft Company.

January 1973

"Prepared by Douglas Aircraft Company, McDonnell Douglas Corporation ... for Langley Research Center...

Computation of the transonic perturbation flow fields around two- and three-dimensional oscillating wings /

Weatherill, W. H.
Sebastian, James D.
Ehlers, F. Edward.
Langley Research Center.
Boeing Commercial Airplane Company.

"Prepared by the Boeing Commercial Airplane Company ... for Langley Research Center.""December 1975....

Flow field analysis of aircraft configurations using a numerical solution to the three-dimensional unified supersonic/hypersonic small disturbance equations, part 1

Knight, C. J.
Gunness, R. C., Jr.
Dsylva, E.

February 1972

The unified small disturbance equations are numerically solved using the well-known Lax-Wendroff fin...

Aerodynamic design and analysis system for supersonic aircraft /

Middleton, W. D. (Wilbur D.), 1931-
Coleman, R. G. (Ronald Gene), 1939-
Lundry, J. L.
Langley Research Center.
Boeing Commercial Airplane Company.

"Prepared by Boeing Commercial Airplane Company ... for Langley Research Center.""March 1975."Cover ...

Analytical comparison of hypersonic flight and wind tunnel viscous/inviscid flow fields /

Fivel, H. J.
Mockapetris, L. J.
Masek, R. V. (Robert Vincent)
Langley Research Center.
McDonnell Douglas Astronautics Company-East.

"Prepared by McDonnell Douglas Astronautics Company-East ... for Langley Research Center.""February ...

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...

Experimental and calculated flow fields produced by airplanes flying at supersonic speeds /

Smith, Harriet J.
United States. National Aeronautics and Space Administration.

Cover title."November 1960."Aerodynamics aircraft; Aircraft safety and noise.Includes bibliographica...

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...

Second-order small-disturbance solutions for hypersonic flow over power-law bodies /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 57-58).Mode ...

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...

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...

Analysis of transonic flow about lifting wing-body configurations /

Barnwell, Richard W.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 69-71).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

An approximate method for calculating three-dimensional inviscid hypersonic flow fields /

Riley, Christopher J. (Christopher Joseph), 1964-
DeJarnette, Fred R.
Langley Research Center.

January 1990

Prepared at Langley Research Center.Bibliography: p. 12.Mode of access: Internet

An improved supersonic, three-dimensional, external, inviscid flow field code /

Marconi, Frank.
Koch, Frank, 1931- joint author.
Grumman Aerospace Corporation.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

March 1979.Prepared for Langley Research Center under contract NAS1-14162.Includes bibliographical r...

Some problems of the calculation of three-dimensional boundary-layer flows on general configurations /

Cebeci, Tuncer.
Langley Research Center.
Douglas Aircraft Company.

January 1973

"Prepared by Douglas Aircraft Company, McDonnell Douglas Corporation ... for Langley Research Center...

Computation of the transonic perturbation flow fields around two- and three-dimensional oscillating wings /

Weatherill, W. H.
Sebastian, James D.
Ehlers, F. Edward.
Langley Research Center.
Boeing Commercial Airplane Company.

"Prepared by the Boeing Commercial Airplane Company ... for Langley Research Center.""December 1975....

Flow field analysis of aircraft configurations using a numerical solution to the three-dimensional unified supersonic/hypersonic small disturbance equations, part 1

Knight, C. J.
Gunness, R. C., Jr.
Dsylva, E.

February 1972

The unified small disturbance equations are numerically solved using the well-known Lax-Wendroff fin...

Aerodynamic design and analysis system for supersonic aircraft /

Middleton, W. D. (Wilbur D.), 1931-
Coleman, R. G. (Ronald Gene), 1939-
Lundry, J. L.
Langley Research Center.
Boeing Commercial Airplane Company.

"Prepared by Boeing Commercial Airplane Company ... for Langley Research Center.""March 1975."Cover ...

Analytical comparison of hypersonic flight and wind tunnel viscous/inviscid flow fields /

Fivel, H. J.
Mockapetris, L. J.
Masek, R. V. (Robert Vincent)
Langley Research Center.
McDonnell Douglas Astronautics Company-East.

"Prepared by McDonnell Douglas Astronautics Company-East ... for Langley Research Center.""February ...

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...

Experimental and calculated flow fields produced by airplanes flying at supersonic speeds /

Smith, Harriet J.
United States. National Aeronautics and Space Administration.

Cover title."November 1960."Aerodynamics aircraft; Aircraft safety and noise.Includes bibliographica...

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...

Second-order small-disturbance solutions for hypersonic flow over power-law bodies /

Townsend, James C. (James Courtland), 1938-
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 57-58).Mode ...

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...

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...

Analysis of transonic flow about lifting wing-body configurations /

Barnwell, Richard W.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 69-71).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

An approximate method for calculating three-dimensional inviscid hypersonic flow fields /

Riley, Christopher J. (Christopher Joseph), 1964-
DeJarnette, Fred R.
Langley Research Center.

January 1990

Prepared at Langley Research Center.Bibliography: p. 12.Mode of access: Internet

An improved supersonic, three-dimensional, external, inviscid flow field code /

Marconi, Frank.
Koch, Frank, 1931- joint author.
Grumman Aerospace Corporation.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1979

March 1979.Prepared for Langley Research Center under contract NAS1-14162.Includes bibliographical r...

Some problems of the calculation of three-dimensional boundary-layer flows on general configurations /

Cebeci, Tuncer.
Langley Research Center.
Douglas Aircraft Company.

January 1973

"Prepared by Douglas Aircraft Company, McDonnell Douglas Corporation ... for Langley Research Center...

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

Abstract

Extracted data

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

Abstract

Extracted data

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