16th AIAA Applied Aerodynamics Conference 1998
DOI: 10.2514/6.1998-2622
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Investigation of confluent boundary layers in high-lift flows

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Cited by 13 publications
(7 citation statements)
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“…In light of this, the time-accurate solutions suggest that the non-realistic variation in pressure seen in the steady-state calculations is partially the result of using a variable timestep (constant CFL number). Similar phenomenon have been observed in calculations with separated flow on multi-element airfoil calculations at high lift 13 , and in calculations of a lobed nozzle with a large separated base region 14 .…”
Section: Mach 09 Nprsupporting
confidence: 56%
“…In light of this, the time-accurate solutions suggest that the non-realistic variation in pressure seen in the steady-state calculations is partially the result of using a variable timestep (constant CFL number). Similar phenomenon have been observed in calculations with separated flow on multi-element airfoil calculations at high lift 13 , and in calculations of a lobed nozzle with a large separated base region 14 .…”
Section: Mach 09 Nprsupporting
confidence: 56%
“…In Ref. 20 approach was required to obtain converged solutions for calculation of a multi-element airfoil exhibiting large-scale separation at high angles of attack. In Ref.…”
Section: A Mach 030 Nozzle Flowmentioning
confidence: 99%
“…The flow over an airfoil is inherently complex and exhibits a variety of physical phenomena including strong pressure gradients, flow separation, and confluence of boundary layers and wakes [e.g., Khorrami et al (1999Khorrami et al ( , 2000, Ying et al (1998), Mathias et al (1999)]. The complex unsteady flow is difficult to compute by traditional computational fluid dynamics (CFD) techniques based on Reynolds-averaged Navier-Stokes (RANS) equations (Rumsey and Ying, 2002).…”
Section: Introductionmentioning
confidence: 99%