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an adverse pressure gradient but not enoughto causesignificant boundary - layer separation
Pressure ... the adverse pressure gradientwould causethe boundary layer separation reduces
an adverse pressure gradient on the upper surface of the wingleadsto boundary layer separation
the formation of an adverse pressure gradient at the undersurface of the trim tab 21(passive) is caused byThis boundary layer separation
an increase in area , an adverse pressure gradient and poor diffusioncan causeboundary layer separation
At \(Ra > Ra_{c}\ ) , the adverse pressure gradient tendsto causeboundary layer separation
the adverse pressure gradient , or thermal choking caused by excessive heat release driving the flow to sonic conditions(passive) caused byboundary - layer separation
a combination of the viscous forces within the fluid boundary layer and an adverse pressure gradient over the flow surface 10(passive) is caused byBoundary layer separation
- 14 Application of suction to the membraneto preventboundary layer separation
the pressure and the strong shockcausesboundary layer separation
the possibility of a shock wave forming that is strong enoughto causeboundary layer separation
conditions of separation in transonic flow ... shock wave and boundary layercan causeboundary layer separation
aft of the shock wave ... and that section of the wing fails to produce lift(passive) is createda boundary layer separation
the presence of strong shock wavescould causeboundary layer separation
The resulting shock wave - boundary layer interaction on the suction sidecausesa boundary - layer separation
the strong shock wave - boundary layer interaction , which determines an increase in the viscous losses(passive) caused bythe boundary layer separation
an interaction between the boundary layer and the shock wave between the first and second compression rampscausedthe separation of boundary layer
shock / boundary - layer interactionscan causefurther boundary - layer separation
the difference in coefficient of thermal expansion between the substrate 110 and the protective layer 150(passive) caused byboundary separation
formation of shock waves(passive) caused bythe boundary layer separation
The drawbacks of the normal shock wave generated inside the isolator due to an increase in the divergent angleleadsto boundary layer separation
the appearance of a strong shock on the upper surface of the airfoilcausesboundary layer separation
a strong shock present at the upper surface of the conventional airfoilto causea boundary layer separation
interaction between the wall and shock train(passive) caused bythe boundary layer separation
Interaction with the cross - flow shockcausesthe boundary layer separation
The further development of this vortexleadsto the boundary layer separation
a negative pressure gradient which helpsto preventboundary layer separation
a. reduction of pressure below vapour pressure c.(passive) is caused byBoundary layer separation
The present disclosure ... to helppreventseparation of a boundary layer
the strong adverse pressure gradients induced by the shock(passive) is caused byThe boundary layer separation
reduced vortex washcausesseparation of boundary layer
intersecting wave interactionscan leadto boundary layer separation
APGs and turbulence effects(passive) is caused bythe boundary layer separation ,
flow sepparation ... they also serveto preventboundry layer separation
the Mach number upstream of the terminal normal shock ... about 1.5to preventboundary layer separation
This creates a faster supersonic flow , followed by a stronger normal shockcausingboundary layer separation
the reduction of velocity in the boundary layer , combined with a positive pressure gradient(passive) is caused byboundary layer separation
a variety of methods including active grids , fractal grids and the classical grids Effects of pressure gradient - both favourable and adverseleadingto boundary layer separation
the wing being run at additional angle of attack(passive) caused byboundary layer separation
transition to turbulence along the fish 's surfaceleadsto boundary layer separation
in a large increase in the drag on the bodyresultsin a large increase in the drag on the body
in consistent readings at high altitudes.09 - 11 - 2014 20140180638METHODresultingin consistent readings at high altitudes.09 - 11 - 2014 20140180638METHOD
a turbulent wakecausinga turbulent wake
to loss of lift , higher drag and subsequently , energyleadsto loss of lift , higher drag and subsequently , energy
in decrease of drag , increasing aerodynamic efficiency , manoeuvrability and also the angle of stallresultingin decrease of drag , increasing aerodynamic efficiency , manoeuvrability and also the angle of stall
the flow - induced noise(passive) caused bythe flow - induced noise
stall at too high an angle of attack ( typically around 16 °causesstall at too high an angle of attack ( typically around 16 °
stall resulting in a low efficiencycan causestall resulting in a low efficiency
in the flow leaving the surface in turbulenceresultingin the flow leaving the surface in turbulence
to total seperation of the flow and stallingleadsto total seperation of the flow and stalling
to the formation of vortices behind the body that could eventually detach periodically into the wakeleadsto the formation of vortices behind the body that could eventually detach periodically into the wake
to partial loss of lift and higher aerodynamic losses on low - pressure turbine ( LPTcan leadto partial loss of lift and higher aerodynamic losses on low - pressure turbine ( LPT
a fluid to flow against a local pressure gradientcausesa fluid to flow against a local pressure gradient
in unstable inlet flow and losses in ramwould resultin unstable inlet flow and losses in ram
to As the upstream length increases the flow once again stabilizesleadsto As the upstream length increases the flow once again stabilizes
a separation bubble between the primary flow and the bounding surfacecreatesa separation bubble between the primary flow and the bounding surface
to the phenomenon of ' wake ' behind a bodyleadsto the phenomenon of ' wake ' behind a body
to a larger wake and hence a larger velocity defectwould leadto a larger wake and hence a larger velocity defect
Stall , and the associated loss of hydrodynamic lift and rise of drag(passive) is caused byStall , and the associated loss of hydrodynamic lift and rise of drag
in decrease of pressure drag and also increase in the angle of stallresultingin decrease of pressure drag and also increase in the angle of stall
to separated flow along the low pressure surface 328leadsto separated flow along the low pressure surface 328
these vortical structures formed by rolling up of viscous flow sheetcausesthese vortical structures formed by rolling up of viscous flow sheet
by blowing The structure of the vorticity field in turbulent channel flowInfluencedby blowing The structure of the vorticity field in turbulent channel flow
to a turbulent flow regime which adversely affects the stream cleaning capabilitiesleadsto a turbulent flow regime which adversely affects the stream cleaning capabilities
from the application of an optical input signal to an optically absorbent flow passageresultingfrom the application of an optical input signal to an optically absorbent flow passage
to stall and vortex shedding that can causes noise and structural vibrations in the blade 10may also leadto stall and vortex shedding that can causes noise and structural vibrations in the blade 10
to a deviation between the geometric camber lines of the blower blades and the actual flow streamlinesleadsto a deviation between the geometric camber lines of the blower blades and the actual flow streamlines
from the back - flow at the shroud contour close to the impeller exit and back disk frictionresultingfrom the back - flow at the shroud contour close to the impeller exit and back disk friction
inconsistent flow velocities resulting from flow oscillation ( variation ) , which affects measurement accuracymay causeinconsistent flow velocities resulting from flow oscillation ( variation ) , which affects measurement accuracy
by making the wedge 's angle of dip sufficiently shallow : that is , by streamlining the wedge , which has the effect of reducing the deceleration of the flow on the wedge 's back surfacecan be preventedby making the wedge 's angle of dip sufficiently shallow : that is , by streamlining the wedge , which has the effect of reducing the deceleration of the flow on the wedge 's back surface
a shear - layercreatesa shear - layer
in reduced form dragthus resultingin reduced form drag
a completely separated or stalled conditioncausinga completely separated or stalled condition
the large - scaled coherent structures(passive) caused bythe large - scaled coherent structures
the vanishing wall shear stress ... and thus makes the wall function approach invalidcreatesthe vanishing wall shear stress ... and thus makes the wall function approach invalid
in high - output bass with low distortionresultingin high - output bass with low distortion
a high pressure part before separation point and a low pressure part after thatcausesa high pressure part before separation point and a low pressure part after that
the vortex rebound near the ground plane(passive) is caused bythe vortex rebound near the ground plane
the strength of evidence required for either of the response options to be initiatedsetsthe strength of evidence required for either of the response options to be initiated
to the secondary and tertiary vortex phenomenaleadingto the secondary and tertiary vortex phenomena