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Aircraft Vortex Wake Dynamics
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English
Abstract
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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Citation
Gaifullin, A. and Soudakov, G., "Aircraft Vortex Wake Dynamics," SAE Technical Paper 965547, 1996, https://doi.org/10.4271/965547.Also In
References
- Adams M.S. Sears W.R. Slender-body theory - review and extensions Journal of Aeronautical Sciences 20 2 1953
- Crow S.C. Stability Theory for a Pair of Trailing Vortices AIAA Journal 12 2172 2179 1970