Calculation of Transonic Aileron Buzz
Copyright policy )Calculation of Transonic Aileron Buzz
An implicit finite-difference computer code that uses a two-layer algebraic eddy viscosity model and exact geometric specification of the airfoil has been used to simulate transonic aileron buzz. The calculated results, which were performed on both the Illiac IV parallel computer processor and the Control Data 7600 computer, are in essential agreement with the original expository wind-tunnel data taken in the Ames 16-Foot Wind Tunnel just after World War II. These results and a description of the pertinent numerical techniques are included.
- Ames Research Center United States
- National Aeronautics and Space Administration United States
Finite difference methods for boundary value problems involving PDEs, Transonic flows, transonic aileron buzz, two- layer algebraic eddy viscosity model, implicit finite-difference computer code
Finite difference methods for boundary value problems involving PDEs, Transonic flows, transonic aileron buzz, two- layer algebraic eddy viscosity model, implicit finite-difference computer code
selected citations These citations are derived from selected sources.This is an alternative to the "Influence" indicator, which also reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).84 popularity This indicator reflects the "current" impact/attention (the "hype") of an article in the research community at large, based on the underlying citation network.Top 10% influence This indicator reflects the overall/total impact of an article in the research community at large, based on the underlying citation network (diachronically).Top 1% impulse This indicator reflects the initial momentum of an article directly after its publication, based on the underlying citation network.Top 10%
Citations provided by BIP!Popularity provided by BIP!