A finite-difference method for predicting supersonic turbulent boundary-layer flows with tangential slot injection /

A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings /

Cebeci, Tuncer.
Ramsey, Judy A., joint author.
Kaups, Kalle, joint author.
McDonnell Douglas Corporation.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1977

Issued Jan. 1977.Prepared by McDonnell Douglas Corporation for Langley Research Center under NAS1-12...

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)...

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...

Calculation by a finite difference method of supersonic turbulent boundary layers with tangential slot injection

Bushnell, D. M.
Beckwith, I. E.

April 1971

Finite difference calculation based on eddy diffusivity and mixing length flow theory to characteriz...

A finite difference method for the solution of the transonic flow around harmonically oscillating wings /

Ehlers, F. Edward.
Langley Research Center.
Boeing Commercial Airplane Company.

January 1974

"Prepared by Boeing Commercial Aircraft Company ... for Langley Research Center."Cover title.Bibliog...

A potential-flow/boundary layer method for calculating subsonic and transonic airfoil flow with trailing-edge separation /

Barnwell, Richard W.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

Subject Category 02."Langley Research Center.""June 1981"--Cover.Includes bibliographical references...

A finite difference method for predicting supersonic turbulent boundary layer flows with tangential slot injection

Lewis, C. H.
Miner, E. W.

October 1972

An implicit finite difference method has been applied to tangential slot injection into supersonic t...

The practical application of a finite difference method for analyzing transonic flow over oscillating airfoils and wings /

Ehlers, F. Edward, joint author.
Sebastian, James D., joint author.
Boeing Commercial Airplane Company.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1978

Issued Feb. 1978.Prepared for Langley Research Center under Contact NAS 1-14204.Includes bibliograph...

Pressure gradient effects on supersonic boundary layer turbulence : final report /

Laderman, A. J.
Ford Aerospace & Communications Corporations Corporation. Aeronutronic Division. Fluid Mechanics Section.

January 1979

"Carried out by the Fluid Mechanics Section of the Aeronutronic Division of the Ford Aerospace & Com...

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 ...

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...

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...

A finite-difference analysis of the nozzle starting process in an expansion tunnel /

Weilmuenster, K. James.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 25-26).Mode ...

Semiempirical method for predicting effects of incident-reflecting shocks on the turbulent boundary layer /

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

Prepared at Langley Research Center."October 1965"--Cover.Includes bibliographical references (p. 38...

An experimental investigation of vortex generation in a turbulent boundary layer undergoing adverse pressure gradient /

Zakkay, Victor.
Calarese, Wladimiro.
Langley Research Center.
New York University.

January 1972

"Prepared by New York University ... for Langley Research Center."Cover title.Bibliography: p. 9.Mod...

A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings /

Cebeci, Tuncer.
Ramsey, Judy A., joint author.
Kaups, Kalle, joint author.
McDonnell Douglas Corporation.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1977

Issued Jan. 1977.Prepared by McDonnell Douglas Corporation for Langley Research Center under NAS1-12...

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)...

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...

Calculation by a finite difference method of supersonic turbulent boundary layers with tangential slot injection

Bushnell, D. M.
Beckwith, I. E.

April 1971

Finite difference calculation based on eddy diffusivity and mixing length flow theory to characteriz...

A finite difference method for the solution of the transonic flow around harmonically oscillating wings /

Ehlers, F. Edward.
Langley Research Center.
Boeing Commercial Airplane Company.

January 1974

"Prepared by Boeing Commercial Aircraft Company ... for Langley Research Center."Cover title.Bibliog...

A potential-flow/boundary layer method for calculating subsonic and transonic airfoil flow with trailing-edge separation /

Barnwell, Richard W.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Langley Research Center.

January 1981

Subject Category 02."Langley Research Center.""June 1981"--Cover.Includes bibliographical references...

A finite difference method for predicting supersonic turbulent boundary layer flows with tangential slot injection

Lewis, C. H.
Miner, E. W.

October 1972

An implicit finite difference method has been applied to tangential slot injection into supersonic t...

The practical application of a finite difference method for analyzing transonic flow over oscillating airfoils and wings /

Ehlers, F. Edward, joint author.
Sebastian, James D., joint author.
Boeing Commercial Airplane Company.
Langley Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1978

Issued Feb. 1978.Prepared for Langley Research Center under Contact NAS 1-14204.Includes bibliograph...

Pressure gradient effects on supersonic boundary layer turbulence : final report /

Laderman, A. J.
Ford Aerospace & Communications Corporations Corporation. Aeronutronic Division. Fluid Mechanics Section.

January 1979

"Carried out by the Fluid Mechanics Section of the Aeronutronic Division of the Ford Aerospace & Com...

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 ...

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...

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...

A finite-difference analysis of the nozzle starting process in an expansion tunnel /

Weilmuenster, K. James.
Langley Research Center.

January 1975

Prepared at Langley Research Center.Cover title.Includes bibliographical references (p. 25-26).Mode ...

Semiempirical method for predicting effects of incident-reflecting shocks on the turbulent boundary layer /

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

Prepared at Langley Research Center."October 1965"--Cover.Includes bibliographical references (p. 38...

An experimental investigation of vortex generation in a turbulent boundary layer undergoing adverse pressure gradient /

Zakkay, Victor.
Calarese, Wladimiro.
Langley Research Center.
New York University.

January 1972

"Prepared by New York University ... for Langley Research Center."Cover title.Bibliography: p. 9.Mod...

A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings /

Cebeci, Tuncer.
Ramsey, Judy A., joint author.
Kaups, Kalle, joint author.
McDonnell Douglas Corporation.
Langley Research Center.
United States. National Aeronautics and Space Administration.

January 1977

Issued Jan. 1977.Prepared by McDonnell Douglas Corporation for Langley Research Center under NAS1-12...

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)...

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...

A finite-difference method for predicting supersonic turbulent boundary-layer flows with tangential slot injection /

Abstract

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A finite-difference method for predicting supersonic turbulent boundary-layer flows with tangential slot injection /

Abstract

Extracted data

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