Computational fluid dynamics (CFD) technology was used to investigate the flow field distribution characteristic of a clamshell thrust reverser with landing flap deployed.The computational grid was generated with unstructured tetrahedron and hexahedron meshes

and Spalart-Allmaras (S-A) turbulent model based on solving Reynolds-averaged Navier-Stokes (RANS) equations was adopted.The results show that

in the range of landing speed

the hot reverse exhaust flow from the clamshell thrust reverser is not re-injected into the engine inlet

but it impinges on part of the aerofoil and pylon.As landing speed decreases

the hot reverse exhaust flow spreads forward and laterally deeper

so it may be re-injected by near engine inlet if the aerofoil sweepback is large enough

resulting possibly in inlet distortion.When landing speed decreases down to 34m/s

the hot reverse exhaust flow starts to impinge on the ground

which may wind up some dross to the inlet.At last

the reverse thrust decreases as landing speed decreases.