Numerical experiment with inviscid vortex‐stretched flow around a cranked Delta wing: supersonic speed
Abstract
A numerical method that solves the Euler equations for compressible flow is used to study vortex stretching. The particular case simulated is supersonic flow M∞=1.2 α=10 degrees around the twisted and cambered cranked‐and‐cropped TKF delta wing of MBB. This geometry induces multiple leading‐edge vortices in a straining velocity field that brings about flow instabilities but the result is a state of statistical equilibrium. The discretization contains over 600,000 cells and offers sufficient degrees of freedom in the solution to resolve the small‐scale unstable modes that lead to disordered vortex flow.
Citation
Rizzi, A. and Purcell, C.J. (1986), "Numerical experiment with inviscid vortex‐stretched flow around a cranked Delta wing: supersonic speed", Engineering Computations, Vol. 3 No. 3, pp. 230-234. https://doi.org/10.1108/eb023661
Publisher
:MCB UP Ltd
Copyright © 1986, MCB UP Limited