Aero-Optics of Supersonic Boundary Layers

Gordeyev, Stanislav; Jumper, Eric J.; Hayden, Tim E.

doi:10.2514/6.2011-1325

Cited by 15 publications

(29 citation statements)

References 11 publications

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“…Several theoretical models were proposed [6,4] to predict levels of aero-optical distortions caused by supersonic boundary levels at different Mach and Reynolds numbers, but the additional experimental data are needed to fully verify them.…”

Section: Introductionmentioning

confidence: 98%

“…While aero-optics of subsonic boundary layers has been extensively studied in recent years [2, 3 and references therein], experimental measurements [4,6] and numerical simulations [7,8,9] in supersonic boundary layers are very limited and many important questions about the details of underlying aero-optical structure, its dynamics still remain unanswered. Several theoretical models were proposed [6,4] to predict levels of aero-optical distortions caused by supersonic boundary levels at different Mach and Reynolds numbers, but the additional experimental data are needed to fully verify them.…”

Section: Introductionmentioning

confidence: 99%

“…While the turbulence levels inside turbulent boundary levels are smaller than turbulence intensity downstream of turrets, boundary layers, especially at transonic and supersonic speeds, might still cause significant aero-optical distortions causing efficiency degradation in directed energy systems [2,3,4] or disrupting free-space highbandwidth airborne communication systems [5]. In addition, studying time-resolved aero-optical distortions provides valuable information into the dynamics of large-scale structures of the turbulent boundary layer [3].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Shack-Hartmann Wavefront Measurements of Supersonic Turbulent Boundary Layers in the TGF

Smith

Gordeyev

Ahmed

et al. 2014

45th AIAA Plasmadynamics and Lasers Conference

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Aero-optical environment of the supersonic flow in Trisonic Gasdynamic Facility (TGF) wind tunnel at Wright-Patterson AFB was experimentally measured using a high-speed wavefront sensor. Temporally-and spatially-resolved wavefronts were collected at a range of Mach numbers between 1.5 and 3.0 and the range of Reynolds numbers between 1 and 4 million per foot. Several data reduction techniques, including multi-point spectral crosscorrelation method, were introduced to analyze results and important statistical information about the turbulent boundary layer was extracted and discussed. A novel method was presented for using the frozen flow assumption to recover time-resolved wavefront measurements from spatially resolved 2-D wavefronts that are under-sampled in time. The criteria for using this technique were discussed in detail.

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Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Shack-Hartmann Wavefront Measurements of Supersonic Turbulent Boundary Layers in the TGF

Smith

Gordeyev

Ahmed

et al. 2014

45th AIAA Plasmadynamics and Lasers Conference

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“…A Pitot tube mounted downstream of the optical measurement location was used to measure the free-stream velocity throughout the experiment. Wavefront measurements were acquired downstream of the heated wall boundary layer development section in both facilities using the Malley Probe 1-D wavefront sensor, which is shown schematically in Figure 3 and is described in detail by Gordeyev, et al [13]. Malley probe data were acquired in the Notre Dame TWT at a streamwise location of 105 cm at freestream velocities V ∞ = 65 to 140 m/s.…”

Section: Methodsmentioning

confidence: 99%

“…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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Structure of the refractive index distribution of the supersonic turbulent boundary layer

Gao

Jiang

et al. 2013

Optics and Lasers in Engineering

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Aero-Optics of Supersonic Boundary Layers

Cited by 15 publications

References 11 publications

Shack-Hartmann Wavefront Measurements of Supersonic Turbulent Boundary Layers in the TGF

Shack-Hartmann Wavefront Measurements of Supersonic Turbulent Boundary Layers in the TGF

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

Structure of the refractive index distribution of the supersonic turbulent boundary layer

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