Fundamental and Experimental Aerodynamics

DAFE Computation Codes

Jet exhaust from a nozzle
in phase with starting on the ground
Computation with Launder-Sharma k-epsilon turbulence model

Among the computation codes used at DAFE:

1. Boundary layer type codes for rapid evaluation of turbulent boundary layers.
    
2. Multicomponent codes
    
   • Used in the Industrial Design Office.
      
   • Low-cost prediction of general aerothermal quantities on projectile or propelled missile afterbodies.
      
3. NASCA Navier-Stokes research code (currently available in 2D and axisymmetric versions):
    
   • Modelling of hypersonic laminar separated flows
      
   • Modelling of turbulent separated flows: afterbody flows and internal flows and jets

Thermal spectrum of a jet exhaust
consisting of air at 3000 K (NASCA)

Thermal spectrum when the jet consists
of combustion species at 3000 K (NASCA)

Last Update: 18 October 2006 - © ONERA 2009 - Terms of use