AbstractSmall disturbance equations for the downstream flow of a transonic aircraft are derived from the steady, viscous, compressible Reynolds-averaged Navier–Stokes equations. These equations are then simplified further for the relevant case of high Reynolds numbers. The given analysis appears not to be trivial, implying a mild form of ambiguity, leading to two acceptable strategies to solve the equations. The physical mechanisms that play a role in vortex decay and the consequent downstream transition of crossflow kinetic energy into viscous/thermodynamic streamwise momentum deficit are identified. The case of discrete trailing vortices having a distinct vortex core is briefly discussed. Four invariant vorticity moments playing a role in the wake roll-up process are re-derived.
The downstream flow of a transonic aircraft: a small disturbance, high Reynolds number analysis
Aerospace Science and Technology ; 12 , 6 ; 457-468
2007-11-06
12 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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