Abstract



A method is presented to construct computationally efficient reducedorder models (ROMs) of threedimensional aerodynamic flows around commercial aircraft components. The method is based on the proper orthogonal decomposition (POD) of a set of steady snapshots, which are calculated using an industrial solver based on some Reynolds averaged NavierStokes (RANS) equations. The PODmode amplitudes are calculated by minimizing a residual defined from the Euler equations, even though the snapshots themselves are calculated from viscous equations. This makes the ROM independent of the peculiarities of the solver used to calculate the snapshots. Also, both the POD modes and the residual are calculated using points in the computational mesh that are concentrated in a close vicinity of the aircraft, which constitute a much smaller number than the total number of mesh points. Despite these simplifications, the method provides quite good approximations of the flow variables distributions in the whole computational domain, including the boundary layer attached to the aircraft surface and the wake. Thus, the method is both robust and computationally efficient, which is checked considering the aerodynamic flow around a horizontal tail plane, in the transonic range 0.4?Mach number?0.8, ?3°?angle of attack?3°.  
International

Si 
JCR

Si 
Title

Journal of Aerospace Engineering 
ISBN

08931321 
Impact factor JCR

0,924 
Impact info


Volume

25 

10.1061/(ASCE)AS.19435525.0000148 
Journal number

4 
From page

588 
To page

599 
Month

JUNIO 
Ranking
