VMFL051
VMFL051
Isentropic
Expansion of Supersonic Flow Over a Convex Corner
Overview
| Reference |
John Anderson. Modern Compressible Flow: With Historical Perspective. McGraw-Hill Science/Engineering/Math, 2002 | ||
| Solver | Ansys Fluent, Ansys CFX | ||
| Physics/Models |
Compressible, inviscid flow | ||
| Input File |
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| Project Files | Link to Project Files Download Page |
Test Case
Centered expansion of inviscid supersonic flow around a corner is modeled. The expansion results in a change in direction of the flow, a drop in static pressure, and increase in Mach number. The approaching flow is supersonic, with a Mach number of 2.5. The expansion process is reversible and adiabatic.
| Material Properties | Geometry | Boundary Conditions | |||
|---|---|---|---|---|---|
|
Density: Ideal Gas law Specific Heat = 1006.43 J/kg-K Molecular weight = 28.966 |
Angle round the corner = 195° |
Inlet:
Wall is adiabatic. |
Analysis Assumptions and Modeling Notes
The flow is steady, inviscid, and incompressible. Analytic expressions for isentropic expansion can be used to calculate the Mach number downstream of the corner.