1996-10-01

Aircraft Vortex Wake Dynamics 965547

The work deals with the problem on aircraft vortex wake behavior in steady-flow formulation. Further approximations of slender-body theory are constructed with the aid of asymptotic methods. The mathematical approach proposed performs to calculate the aircraft wake up to breakdown. The nontrivial analytic solutions for the problem of motion of one and two vortex filaments with circular cross-section are obtained.

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