Aero-Optic Distortion in Transonic and Hypersonic Turbulent Boundary Layers

Wyckham, Christopher; Smits, Alexander J.

doi:10.2514/1.41453

Cited by 91 publications

(64 citation statements)

References 9 publications

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“…This scaling is consistent with the scaling of Wyckham and Smits 17 in the limit of moderate subsonic speeds and adiabatic wall conditions. Bucker et al 12 verified this scaling using a simple vortical structure model, though his model over-estimated the experimental OPD rms values by a factor of 4.…”

Section: Introductionsupporting

confidence: 77%

“…A significant advancement in the field came from Morkovin's 1962 presentation of the Strong Reynolds Analogy (SRA) [15][16][17] , which presumes that p′ is negligible. From this analogy between the Reynolds-averaged form of the energy and momentum equations, a relationship between the fluctuating static temperature and fluctuation velocity is achieved, such that,…”

Section: Introductionmentioning

confidence: 99%

“…The reader is directed to [10] for further information and a discussion of the Malley probe setup, operation, and data analysis. Wyckham and Smits 17 used a two-dimensional Shack-Hartmann sensor to study aero-optical properties of subsonic and supersonic boundary layers and developed a scaling law for these aberrations as a function of the freestream Mach number, the local skin friction coefficient, c f , and the ratio of the freestream static temperature, T ∞ , to the wall temperature, T w ,…”

Section: Introductionmentioning

confidence: 99%

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Aero-Optical Measurements in a Heated, Subsonic, Turbulent Boundary Layer

Cress

Gordeyev

Jumper

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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A scaling relationship for OPD rms that accounts for the fluctuating total temperature profile within a turbulent boundary is derived from the modified Crocco relation. Experimental data from heated, compressible boundary layers at six subsonic Mach numbers in two wind tunnel facilities are shown to be consistent with the theory. The results show that a temperature mismatch between the freestream and underlying wall has a significant impact on the overall optical aberration.

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Section: Introductionsupporting

confidence: 77%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aero-Optical Measurements in a Heated, Subsonic, Turbulent Boundary Layer

Cress

Gordeyev

Jumper

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…where G(M) = 1 -0.19M 2 + 0.03M 4 for M < 1.5 and showed that this scaling law give very similar prediction compared to the scaling law by Wyckham & Smits [8]. Since for M < 0.4, 1 > G(M) > 0.97, the scaling may be simplified by neglecting the G(M) term for the remainder of this paper.…”

Section: Opl X Y T N X Y Z T Dz K X Y Z T Dzmentioning

confidence: 98%

“…Wyckham & Smits [8] pioneered the use of a high-speed camera and a lenslet array to create a high-bandwidth Shack-Hartmann wavefront sensor, which allowed for measurements of aero-optic aberrations with good spatial and temporal resolution. Using a bulk-flow analysis they derived the more-general scaling law for OPD rms including supersonic regime as [ ] [13,14] derived an alternative general scaling law for OPD rms ,…”

Section: Opl X Y T N X Y Z T Dz K X Y Z T Dzmentioning

confidence: 99%

Subsonic Boundary-Layer Wavefront Spectra for a Range of Reynolds Numbers

Smith

Gordeyev

Saxton-Fox

et al. 2014

45th AIAA Plasmadynamics and Lasers Conference

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Aero-optic measurements of turbulent boundary layers were performed in wind tunnels at the University of Notre Dame and California Institute of Technology for heated walls at a range of Reynolds numbers. Temporally resolved measurements of wavefronts were collected at a range of Mach numbers between 0.03 and 0.4 and the range of Re θ between 1,700 and 20,000. Wavefront spectra for both heated and un-heated walls were extracted and compared to demonstrate that wall heating does not noticeably alter the shape of wavefront spectra in the boundary layer. The effect of Reynolds number on the normalized spectra was also presented, and an empirical spectral model was modified to account for Reynolds number dependence. Measurements of OPD rms for heated walls were shown to be consistent with results from prior experiments, and a method of estimating OPD rms and other boundary layer statistics from wavefront measurements of heated-wall boundary layers was demonstrated and discussed.

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2022

Aero‐Optical Effects

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Aero-Optic Distortion in Transonic and Hypersonic Turbulent Boundary Layers

Cited by 91 publications

References 9 publications

Aero-Optical Measurements in a Heated, Subsonic, Turbulent Boundary Layer

Aero-Optical Measurements in a Heated, Subsonic, Turbulent Boundary Layer

Subsonic Boundary-Layer Wavefront Spectra for a Range of Reynolds Numbers

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