VMFL017
VMFL017
Transonic
Flow over an RAE 2822 Airfoil
Overview
| Reference |
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| Solver | Ansys Fluent, Ansys CFX | ||
| Physics/Models | Compressible, turbulent flow | ||
| Input File |
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| Project Files | Link to Project Files Download Page |
Test Case
Flow over an RAE 2822 airfoil at a free-stream Mach number of 0.73. The angle of attack is 2.79°. The flow field is 2D, compressible (transonic), and turbulent. The geometry of the RAE 2822 airfoil is shown in Figure 42: Geometry of the RAE 2822 Airfoil . It is a thick airfoil with a chord length, c, of 1.00 m and a maximum thickness, d, of 0.121 m. The flow domain spans over 100 Chord lengths in both streamwise and transverse directions, so that the presence of the airfoil is not felt at the outer boundary.
| Material Properties | Geometry | Boundary Conditions |
|---|---|---|
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Fluid: Air
|
Chord length = 1 m Maximum thickness = 0.121 m |
The inlet conditions are: Mach number = 0.73 Re = 6.5 x 106 Static pressure = 43765 Pa Inlet temperature = 300 K Turbulent intensity = 0.05 % Turbulent viscosity ratio = 10 |
Analysis Assumptions and Modeling Notes
The implicit formulation of the density-based solver is used. The SST k-ω turbulence model is used to account for turbulence effects. The problem is solved in steady state mode. The experimental procedure included uses a transition trip to fix the boundary layer transition.