VMFL041

VMFL041
Transonic Flow Over an Airfoil

Overview

Reference P.H. Cook, M.A. McDonald, M.C.P. Firmin. “AEROFOIL RAE 2822 - PRESSURE DISTRIBUTIONS, AND BOUNDARY LAYER AND WAKE MEASUREMENTS.” AGARD Advisory Report No. 138.

Solver Ansys Fluent

Physics/Models Transonic flow, shock, SST model

Input File

VMFL041_transonic.cas

Project Files Link to Project Files Download Page

Test Case

Transonic flow over air foil RAE 2822 is modeled for an angle of attack of 3.19°. The flow domain spans over 100 Chord lengths in both stream-wise and transverse directions.

Figure 105: Flow Domain

Material Properties	Geometry	Boundary Conditions
Density: Ideal gas law for Air Viscosity: 1.831 X 10^-5 kg/m-s	Chord length of the airfoil = 1 m	Velocity profile at inlet with an average velocity of 218 m/s

Material Properties

Geometry

Boundary Conditions

Density: Ideal gas law for Air

Viscosity: 1.831 X 10^-5 kg/m-s

Chord length of the airfoil = 1 m

Velocity profile at inlet with an average velocity of 218 m/s

Analysis Assumptions and Modeling Notes

The flow is steady. The inlet flow Mach number is close to transonic range. Walls are assumed to be adiabatic.

Results Comparison for Ansys Fluent

Figure 106: Comparison of Pressure Coefficient on the Airfoil