Publikationsdatum:
2013-08-31
Beschreibung:
An implicit, two factor, split flux, finite volume Euler equations solution algorithms is applied to the time accurate solution of transonic flow about an NACA 0012 airfoil and a rectangular planform supercritical wing undergoing pitch oscillations. Accuracy for Courant numbers greater than one is analyzed. Freezing the flux Jacobians can result in significant savings for steady state solutions; the accuracy of freezing flux Jacobians for unsteady results is investigated. The Euler algorithm results are compared with experimental results for an NACA 0012 and a rectangular planform supercritical wing.
Schlagwort(e):
AERODYNAMICS
Materialart:
NASA, Langley Research Center, Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 1; p 215-241
Format:
application/pdf
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