Engineering
Two Dimensional
100%
Computer Simulation
100%
Image Visualization
100%
Obtains
100%
Static Pressure
100%
Reynolds' Number
50%
Experimental Result
50%
Good Agreement
50%
Flow Visualization
50%
Free-Stream Mach Number
50%
Pressure Data
50%
Layer Interaction
50%
Turbulent Boundary Layer
50%
Subsonic Diffuser
50%
Pressure Loss
50%
Flow Characteristics
50%
Model Test
50%
Keyphrases
Supersonic Inlet
100%
Pseudo Shock Wave
100%
Visualization Image
66%
Total Pressure Loss
33%
Mente
33%
Boundary Layer Interaction
33%
RANS Equations
33%
Supersonic Wind Tunnel
33%
Unit Reynolds number
33%
Rectangular Shape
33%
Physics
Shock Wave
100%
Supersonics
100%
Image Visualization
50%
Static Pressure
50%
Turbulent Boundary Layer
25%
Reynolds Number
25%
Flow Visualization
25%
Flow Characteristics
25%
Wind Tunnels
25%
Mach Number
25%
Free Flow
25%