Wake measurements in a strong adverse pressure gradient
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Wake measurements in a strong adverse pressure gradient

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Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

Subjects:

  • Flow distribution.,
  • Lift devices.,
  • Pressure effects.,
  • Pressure gradients.,
  • Wakes.,
  • Wind tunnel tests.

Book details:

Edition Notes

StatementR. Hoffenberg, J.P. Sullivan, S.P. Schneider.
SeriesNASA contractor report -- NASA CR-197272.
ContributionsSullivan, J. P., Schneider, Steven P., United States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15411517M

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Wake measurements in a strong adverse pressure gradient. The behavior of wakes in adverse pressure gradients is critical to the performance of high-lift systems for transport aircraft. Wake deceleration is known to lead to sudden thickening and the onset of reversed flow; this 'wake bursting' phenomenon can occur while surface flows remain. focus of the research has been to isolate the effects of both pressure gradient and initial wake asymmetry on the wake development. Experimental results reveal that the pressure gradient has a tremendous influence on the wake development, despite the relatively modest pressure gradients imposed. For a given pressure gradient, the. The aerodynamics of multielement high-lift devices is complex and can be greatly impacted by wakes in an adverse pressure gradient. In addition to the shape and location of each element, the wake of the main element, the jet through the gaps, and the flap wakes can all have a large effect on the flowfield.2,3 If a strong adverse pressure. Although this type of model adjustment has been found to be very successful for flows under strong adverse pressure gradients, it was not able to predict the overshoot of turbulent shear stress in the flow recovery region. A. E. and Joubert, P. N., “A Boundary Layer Developing in an Increasingly Adverse Pressure Gradient,” Journal.

dx= m–1; 2) a constant adverse pressure gradient (APG) condition with dC p/dx= m–1, and; 3) a con-stant favorable pressure gradient (FPG) condition with dC p/dx= – m –1. The zero pressure gradient wake served as an essential baseline case for comparison with the nonzero pressure gradient wake development. In. Direct numerical simulation of a supersonic turbulent boundary layer subject to adverse pressure gradient induced by external successive compression waves AIP Advances, Vol. 9, No. 8 The amplification of large-scale motion in a supersonic concave turbulent boundary layer and its impact on the mean and statistical properties. Book Search tips Selecting this option will search all publications across the D. M. Passchier, and R. A. W. M. Henkes, “ Experimental investigation of an adverse pressure gradient wake and comparison with calculations and S. P. Schneider, “ Wake measurements in a strong adverse pressure gradient,” AIAA Pap. 95– ( Pressure has to rise past the suction peak in order for the air to get back to ambient pressure. The upper side suction is caused by the airfoil's curvature, and curvature over the rear part of the airfoil is very low or even negative - that is what makes the air assume ambient pressure again.

This paper describes an experimental investigation into the development of a planar turbulent wake under constant adverse and favorable pressure gradient conditions. The focus of the study is on the near-wake due to its relevance to high-lift systems for commercial transport aircraft. The wake is generated by a flat splitter plate with tapered trailing edge. Measurements of transitional flow in regions of strong adverse pressure gradient on an axial compressor stator are reported. The range of observations covers separating laminar flow at transition onset, and reattachment of intermittently turbulent periodically separated shear layers. pressure velocity up = p d dP=dx=r vs upy=Ued where Ue is the inviscid outer velocity at the top of the boundary layer and r is the fluids density. This pressure velocity can be used to non-dimensionalize the velocity profiles in strong adverse pressure gradient flows, but just as . Measurements of wall pressure fluctuations in an axisymmetric turbulent boundary layer under a strong adverse pressure gradient are analyzed, in combination with Large Eddy Simulations [12,13].