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On supersonic flow behind a curved shock

OOn supersonic flow behind a curved shock

Número de Cutter-SanbornM613oEntrada «Meyer, M.» → 613 · marca de obra “o”

On supersonic flow behind a curved shock

de R. E. Meyer · Publicada por primera vez en 1956

Ediciones (1)

On supersonic flow behind a curved shock (1956)
Aeronautical Research Laboratories

Más obras de R. E. Meyer

AAnalytical treatment of two-dimensional supersonic flow. Par

Analytical treatment of two-dimensional supersonic flow. Part 1: shock free flow

1955

AA Liouville theorem in unsteady gas dynamics. Part I: A no

A Liouville theorem in unsteady gas dynamics. Part I: A non-existence theorem

1960

On supersonic flow behind a curved shock — R. E. Meyer | Cutter Number

A

A Liouville theorem in unsteady gas dynamics. Part III: A

A Liouville theorem in unsteady gas dynamics. Part III: A limit line theorem

1960

AA Liouville theorem in unsteady gas dynamics. Part II: The

A Liouville theorem in unsteady gas dynamics. Part II: The regular characteristic plane

1960

OOn the measurement of supersonic aerofoil drag by pressure t

On the measurement of supersonic aerofoil drag by pressure traverse

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PPerturbations of supersonic nozzle flows

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