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= Jet in a cross flow  = Underlying Flow Regime 1-05 <font size="-2" color="#888888">               © copyright ER

...y of the effects that the relative end-wall/blade motion introduces to the flow. Four experimental cases arise from the combination of 2 tip-clearance heig ...secondary vortices appearing that interact with other relevant underlying flow regimes as the boundary layers and the wakes of the blades.

===Underlying Flow Regime 2-15=== The flow past a rectangular cylinder of breadth to depth ratio equal to 5 is charact

!Flow Type !! UFR number!! Underlying Flow Regime !! Contributor !! Organisation | style="background-color:LightGrey;"|[[Blade tip and tip clearance vortex flow]]<!--[[Image:Star_red.jpg]]-->|| style="background-color:LightGrey;"| Micha

=Flow in a 3D diffuser= ===Underlying Flow Regime 4-16===

Underlying Flow Regime 3-10 <font size="-2" color="#888888">               © copyright ER ...inner flow resembles a turbulent boundary layer, and the outer part of the flow is similar to a free jet. There also exists a region of negative production

= Flow in a curved rectangular duct - non rotating = Underlying Flow Regime 4-04 <font size="-2" color="#888888"> © copyright ERCOFTAC 2

===Underlying Flow Regime 4-19=== *Biedron R. T., Adamson Jr. T. C., ''“Unsteady Flow in a Supercritical Supersonic Diffuser”'', AIAA Journal, Vol. 26(11), pp.

...ng adverse pressure gradients (the trailing edges being heavily loaded), a regime which is difficult for numerical methods but of great importance in wing de The Mach number is 0.744 and the angle of incidence is 2.5o. Flow separation does not occur and there are no strong shock waves. The boundary

Underlying Flow Regime 4-02 <font size="-2" color="#888888"> © copyright ERCOFTAC 2 ...neering and industrial applications. The swirl mechanism introduced into a flow enhances mixing, heat transfer and plays a major role in stabilization of t

= Flow around (airfoils and) blades (subsonic) = Underlying Flow Regime 2-04 <font size="-2" color="#888888">               © copyright ER

=High Reynolds Number Flow around Airfoil in Deep Stall= ===Underlying Flow Regime 2-11===

=== Underlying Flow Regime 3-34 === ...d="6">'''Uzun A, Malik MR''' (2015) Wall-Resolves Large-Eddy Simulation of Flow Separation over NASA Wall-Mounted Hump. AIAA Paper 2017-0538.</div>

Underlying Flow Regime 3-07 <font size="-2" color="#888888"> © copyright ERCOFTAC 2 ...&ldquo;Combined free and forced convection, II. Heat transfer in opposing flow&rdquo;,'' The Canadian J. Chem. Eng.,'' Dec 1965, pp. 313-318.

=== Underlying Flow Regime 3-32 === the regime, subsonic or supersonic. This is a problem that is important

Underlying Flow Regime 4-10 <font size="-2" color="#888888">               © copyright ER ...ut it can no longer be assumed that these have no effect on their external flow. In the present case only the specific subclass of two-dimensional rectangu

Underlying Flow Regime 3-10 <font size="-2" color="#888888">               © copyright ER ...m cooling and the automobile demister, but it is also an important generic flow in itself.

===Underlying Flow Regime 3-36=== The key flow physics to be accurately captured in this UFR are turbulent boundary layers

= Flow around airfoils (and blades) A-airfoil (Ma=0.15,<br />Re/m=2x10⁶ Underlying Flow Regime 2-05 <font size="-2" color="#888888"> © copyright ERCOFTAC 2

Underlying Flow Regime 3-30 ...ng, B.: Experimental and theoretical investigation of backward-facing step flow, J. Fluid Mech. vol. 127, pp. 473-496