Nol Hypersonic Tunnel No. 4, Results 7: Experimental Investigation of Turbulent Boundary Layers in Hypersonic Flow

Lobb, R. Kenneth; Winkler, E. M.; Persh, Jerome

doi:10.21236/ad0068499

Cited by 15 publications

(7 citation statements)

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“…by Lobb et al (1955), revisited by Huang et al (1995) and Coleman et al (1995) and generalised by Trettel & Larsson (2016). This scaling gives rise to a local Reynolds number (Cebeci & Bradshaw 2012;Patel et al 2015) at each wall-normal location…”

Section: Relatively Subsonic Region and Universality Of Resolvent Modesmentioning

confidence: 99%

Resolvent-based study of compressibility effects on supersonic turbulent boundary layers

2019

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The resolvent formulation of McKeon & Sharma (2010) is extended to the compressible Navier-Stokes equations. Resolvent analysis is applied to the supersonic turbulent boundary layer in order to study the validity of Morkovin's hypothesis, which postulates that high-speed turbulence structure in zero pressure-gradient turbulent boundary layers remains largely the same as its incompressible counterpart. Supersonic turbulent boundary layers with adiabatic wall boundary conditions at Mach numbers ranging from 2 to 4 are considered. Resolvent analysis highlights two distinct regions of the supersonic turbulent boundary layer in the wave parameter space: the relatively supersonic region and the relatively subsonic region. In the relatively supersonic region, where the flow is supersonic relative to the freestream, resolvent modes display structures consistent with Mach wave radiation that are absent in the incompressible regime. In the relatively subsonic region, we show that the low-rank approximation of the resolvent operator is an effective approximation of the full system and that the response modes predicted by the model exhibit universal and geometrically self-similar behaviour via a transformation given by the semi-local scaling. Moreover, with semi-local scaling, we show that the resolvent modes follow the same scaling law as their incompressible counterparts in this region, which has implications for modelling and the prediction of turbulent high-speed wall-bounded flows. We also show that the thermodynamic variables exhibit similar mode shapes to the streamwise velocity modes, supporting the strong Reynolds analogy. Finally, we demonstrate that the principal resolvent modes can be used to capture the energy distribution between momentum and thermodynamic fluctuations.

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Section: Relatively Subsonic Region and Universality Of Resolvent Modesmentioning

confidence: 99%

Resolvent-based study of compressibility effects on supersonic turbulent boundary layers

2019

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“…13 are the linear and quadratic results given by Eqs. (45) and (46). In addition, an analog computer solution was obtained for Eq.…”

Section: Lomentioning

confidence: 99%

“…-TR-76-62(46) which does not require unity Prandtl number. However, Eq (46). does riot conserve energy across the boundary layer for nonunity recovery factor.…”

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confidence: 99%

“…This is easily seen by considering the total energy integral equation (see for exampleShapiro (Ref. 36)), which for an adiabatic flat plate flow can only be satisfied if To takes on values in the boundary layer that are both less' than and greater than To , i.e., there must be total-temperature It is clear that To can never be greater than To ,00 according to Eq (46). assuming U~I.Meier (Ref.…”

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confidence: 99%

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Analytical, Numerical, and Experimental Results on Turbulent Boundary Layers

Whitfield¹

1976

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When U. S. Government drawings specifications, or other data are used for any purpose other than a definitely related Government procurement operation, the Government thereby incurs no responsibility nor any obligation whatsoever, and the fact that the Government may have formulated, furnished, or in any way supplied the said drawings, specifications, or other data, is not to be regarded by implication or otherwise, or in any manner licensing the holder or any other person or corporation, or conveying any rights or permission to manufacture, use, or sell any patented invention that may in any way be related thereto. Qualified users may obtain copies of this report from the Defense Documentation Center. References to named commercial products in this report are not to be considered in any sense as an endorsement of the product by the United States Air Force or the Government. This report has been reviewed by the Information Office (01) and is releasable to the National Technical Information Service (NTIS). At NTIS, it will be available to the general public, including foreign nations. APPROVAL STATEMENT This technical report has been reviewed and is approved for publication.

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“…4 . 5 These studies were of interest primarily for determining effect of the optical path at each station. (The optical path is defined as the product of the total path length and partial pressure of the active component: a measure of the total number of molecules in the path.)…”

Section: A Boundary Layers and Optical Pathmentioning

confidence: 99%