Godunov-type schemes with an inertia term for unsteady full Mach number range flow calculations
, 2014 Yann Moguen +4 more
openalex +2 more sources
Exploratory study of transient upstart phenomena in a three-dimensional fixed-geometry scramjet engine [PDF]
The structural and thermal design of a hydrogen fueled regeneratively cooled three dimensional fixed geometry scramjet was examined. An exploratory study was conducted at Mach 5.3 in the 7-inch Mach 7 pilot tunnel to investigate the unstart phenomena and
Wieting, A. R.
core +1 more source
Hypersonic turbulent wall boundary layer computations [PDF]
The Baldwin-Lomax algebraic turbulence model was modified for hypersonic flow conditions. Two coefficients in the outer layer eddy viscosity model were determined as functions of Mach number and temperature ratio.
Harloff, G. J., Kim, S. C.
core +1 more source
Characteristic variation of Mach number in subsonic co-flowing jets by varying lip thickness. [PDF]
Sci RepKumar KS +5 more
europepmc +1 more source
The stability of a trailing-line vortex in compressible flow [PDF]
We consider the inviscid stability of the Batchelor (1964) vortex in a compressible flow. The problem is tackled numerically and also asymptotically, in the limit of large (aximuthal and streamwise) wavenumbers, together with large Mach numbers.
Duck, Peter W., Stott, Jillian A. K.
core +1 more source
, 2014 Inertia terms are introduced in a Godunoy-type scheme. The resulting scheme, called AUSM-IT, is designed as an extension of the AUSM+-up scheme, in order to allow full Mach number range calculations of unsteady flows. In line with the continuous asymptotic analysis, the AUSM-IT scheme satisfies the exact conservation of the discrete linear acoustic ...
Moguen, Yann +4 more
openaire +2 more sources
Passive control of suddenly expanded flow and temperature distribution along the duct at critical Mach number. [PDF]
Sci RepTamboli S +8 more
europepmc +1 more source
Exploratory wind tunnel tests of a shock-swallowing air data sensor at a Mach number of approximately 1.83 [PDF]
The test probe was designed to measure free-stream Mach number and could be incorporated into a conventional airspeed nose boom installation. Tests were conducted in the Langley 4-by 4-foot supersonic pressure tunnel with an approximate angle of attack ...
Couch, L. M., Nugent, J., Webb, L. D.
core +1 more source
Effects of Mach Number on Non-Rankine–Hugoniot Shock Zone of Mach Reflection [PDF]
, 2018 Haochen Liu +3 more
openalex +1 more source
Experimental and numerical investigation of suddenly expanded flow at sonic mach number. [PDF]
Sci RepKhan A +4 more
europepmc +1 more source