Mach Number

136 books
Revised tables of airspeed, altitude, and Mach number presented in the international system of unitsMargaret S. Benner
⏱ 40m

Revised tables of airspeed, altitude, and Mach number presented in the international system of units

Margaret S. Benner

197340 pp.
Flight investigation at high mach numbers of several methods of measuring static pressure on an airplane wingLangley Aeronautical Laboratory
⏱ 24m

Flight investigation at high mach numbers of several methods of measuring static pressure on an airplane wing

Langley Aeronautical Laboratory

194424 pp.
An evaluation of three two-dimensional computational fluid dynamics codes including low Reynolds numbers and transonic Mach numbersR. M. Hicks

An evaluation of three two-dimensional computational fluid dynamics codes including low Reynolds numbers and transonic Mach numbers

R. M. Hicks

1991No page data
Consistent initial conditions for the DNS of compressible turbulenceJ. R. Ristorcelli

Consistent initial conditions for the DNS of compressible turbulence

J. R. Ristorcelli

1996No page data
Progress in Favré-Reynolds stress closures for compressible flowsV. Adumitroaie

Progress in Favré-Reynolds stress closures for compressible flows

V. Adumitroaie

1998No page data
A study of the effects of Reynolds number and Mach number on constant pressure coefficient jump for shock-induced trailing-edge separationAtlee M. Cunningham
⏱ 1h 19m

A study of the effects of Reynolds number and Mach number on constant pressure coefficient jump for shock-induced trailing-edge separation

Atlee M. Cunningham

198779 pp.
High-lift flight tunnelDavid Lofftus

High-lift flight tunnel

David Lofftus

2000No page data
The effects of viscosity on the stability of a trailing-line vortex in compressible flowJillian A. K. Stott

The effects of viscosity on the stability of a trailing-line vortex in compressible flow

Jillian A. K. Stott

1994No page data
User manual for NASA Lewis 10- by 10-Foot Supersonic Wind TunnelRonald H. Soeder

User manual for NASA Lewis 10- by 10-Foot Supersonic Wind Tunnel

Ronald H. Soeder

1992No page data
A summary of the techniques of variable Mach number supersonic wind tunnel nozzle designJ. T. Kenney
⏱ 2h 13m

A summary of the techniques of variable Mach number supersonic wind tunnel nozzle design

J. T. Kenney

1954133 pp.
Two- and three-dimensional viscous computations of a hypersonic inlet flowUnknown Author

Two- and three-dimensional viscous computations of a hypersonic inlet flow

Unknown Author

1987No page data
Two- and three-dimensional viscous computations of a hypersonic inlet flowUnknown Author

Two- and three-dimensional viscous computations of a hypersonic inlet flow

Unknown Author

1987No page data
Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paintLangley Aeronautical Laboratory
⏱ 20m

Flight investigation at high speeds of profile drag of wing of a P-47D airplane having production surfaces covered with camouflage paint

Langley Aeronautical Laboratory

194620 pp.
Supersonic-tunnel tests of projectiles in Germany and ItalyLangley Aeronautical Laboratory
⏱ 1h 14m

Supersonic-tunnel tests of projectiles in Germany and Italy

Langley Aeronautical Laboratory

194574 pp.
Evaluation of F/A-18A HARV inlet flow analysis with flight dataUnknown Author

Evaluation of F/A-18A HARV inlet flow analysis with flight data

Unknown Author

1995No page data
30th computational fluid dynamicsVon Karman Institute for Fluid Dynamics

30th computational fluid dynamics

Von Karman Institute for Fluid Dynamics

1999No page data
Preliminary flight research on an all-movable horizontal tail as a longitudinal control for flight at high mach numbersLangley Aeronautical Laboratory
⏱ 20m

Preliminary flight research on an all-movable horizontal tail as a longitudinal control for flight at high mach numbers

Langley Aeronautical Laboratory

194520 pp.
Robust airfoil optimization to achieve consistent drag reduction over a mach rangeWu Li

Robust airfoil optimization to achieve consistent drag reduction over a mach range

Wu Li

2001No page data
Flow quality and operational enhancements in the NASA Lewis 8- by 6-Foot Supersonic Wind TunnelE. Allen Arrington

Flow quality and operational enhancements in the NASA Lewis 8- by 6-Foot Supersonic Wind Tunnel

E. Allen Arrington

1998No page data
Impingement of boundary-reflected disturbances originating at the nose of a body of revolution in the Langley Research Center 16-foot transonic tunnelRichard J. Re

Impingement of boundary-reflected disturbances originating at the nose of a body of revolution in the Langley Research Center 16-foot transonic tunnel

Richard J. Re

1998No page data
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