Excitation of Crossflow Instabilities in a Swept Wing Boundary Layer

Carpenter, Mark H.; Choudhari, Meelan M.; Li, Fēi; Streett, Craig L.; Chang, Chau‐Lyan

doi:10.2514/6.2010-378

Cited by 24 publications

(19 citation statements)

References 39 publications

(50 reference statements)

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“…We note that Ref. 49, after detrending the raw data of Ref. 23, the computed rms surface roughness height was 0.09 µm and 6.5 µm for the polished and painted surfaces, respectively, as compared to the raw rms values of .3 µm and 1 µm quoted in Ref.…”

Section: Pse Analysismentioning

confidence: 99%

“…A Compressible LNS code is under-development but is currently not available to carry out receptivity computations for the G-3, similar to those in Carpenter et al 49 In the meantime, it will be instructive to carry out PSE analysis as a risk reduction exercise, particularly since the planned range of flight Reynolds numbers is even higher than the G-2 case of Ref. 45.…”

Section: Pse Analysismentioning

confidence: 99%

“…45 A crucial piece of missing information is the initial disturbance level induced by roughness. Carpenter et al 49 have studied receptivity of incompressible swept-wing boundary layer to surface roughness using Linearized Navier-Stokes (LNS) equations. For the Cessna O-2 case, they were able to demonstrate that disturbance amplitude internalized in the boundary-layer differed by two orders of magnitude (approximately e 5 ) between surface roughness distributions modeled after surface height measurements for painted and polished surfaces, which is roughly consistent with the observation of Saric et al 23 that transition moved forward to about 30% chord when the leading-edge was painted as compared to the transition location at 80% chord for the polished leading-edge.…”

Section: Pse Analysismentioning

confidence: 99%

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Computational Analysis of the G-III Laminar Flow Glove

Malik

Liao

Lee-Rausch

et al. 2011

29th AIAA Applied Aerodynamics Conference

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Under NASA's Environmentally Responsible Aviation Project, flight experiments are planned with the primary objective of demonstrating the Discrete Roughness Elements (DRE) technology for passive laminar flow control at chord Reynolds numbers relevant to transport aircraft. In this paper, we present a preliminary computational assessment of the Gulfstream-III (G-III) aircraft wing-glove designed to attain natural laminar flow for the leading-edge sweep angle of 34.6 o . Analysis for a flight Mach number of 0.75 shows that it should be possible to achieve natural laminar flow for twice the transition Reynolds number ever achieved at this sweep angle. However, the wing-glove needs to be redesigned to effectively demonstrate passive laminar flow control using DREs. As a by-product of the computational assessment, effect of surface curvature on stationary crossflow disturbances is found to be strongly stabilizing for the current design, and it is suggested that convex surface curvature could be used as a control parameter for natural laminar flow design, provided transition occurs via stationary crossflow disturbances.

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Section: Pse Analysismentioning

confidence: 99%

Section: Pse Analysismentioning

confidence: 99%

Section: Pse Analysismentioning

confidence: 99%

See 1 more Smart Citation

Computational Analysis of the G-III Laminar Flow Glove

Malik

Liao

Lee-Rausch

et al. 2011

29th AIAA Applied Aerodynamics Conference

Self Cite

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show abstract

“…26 , with results suggesting that three-dimensional (3D) disturbances are more sensitive than the corresponding 2D instabilities. Adjoint receptivity methods have been applied to a number of flow systems and boundary layer instabilities 27-32 , while Carpenter et al 33 examined crossflow receptivity in the context of a 3D boundary layer and a swept aerofoil. A review of adjoint methods and their many applications are given by Luchini and Bottaro 34 .…”

Section: Introductionmentioning

confidence: 99%

On predicting receptivity to surface roughness in a compressible infinite swept wing boundary layer

2017

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The receptivity of crossflow disturbances on an infinite swept wing is investigated using solutions of the adjoint linearised Navier-Stokes equations. The adjoint based method for predicting the magnitude of stationary disturbances generated by randomly distributed surface roughness is described, with the analysis extended to include both surface curvature and compressible flow effects. Receptivity is predicted for a broad spectrum of spanwise wavenumbers, variable freestream Reynolds numbers and subsonic Mach numbers. Curvature is found to play a significant role in the receptivity calculations, while compressible flow effects are only found to marginally affect the initial size of the crossflow instability. A Monte-Carlo type analysis is undertaken to establish the mean amplitude and variance of crossflow disturbances generated by the randomly distributed surface roughness. Mean amplitudes are determined for a range of flow parameters that are maximised for roughness distributions containing a broad spectrum of roughness wavelengths, including those that are most effective in generating stationary crossflow disturbances. A control mechanism is then developed where the short scale roughness wavelengths are damped, leading to significant reductions in the receptivity amplitude.

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“…75,77,78,79 Saric and Reed 74 detail the pertinence of nonlinear effects when predicting crossow instability growth and transition for incompressible flow. It has been well established that stationary modes, after a period of linear growth, saturate nonlinearly and give rise to secondary instabilities that then rapidly lead to transition (see, for instance, White 80 ).…”

Section: Introductionmentioning

confidence: 99%

HIFiRE-1 and HIFiRE-5 Test Results

Kimmel¹,

Adamczak²,

Borg³

et al. 2014

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information AFRL/RQHF SPONSORING/MONITORING AGENCY REPORT NUMBER(S) AFRL-RQ-WP-TR-2014-0038 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution unlimited SUPPLEMENTARY NOTESPA Case Number: 88ABW-2014-3421; Clearance Date: 17 Jul 2014. ABSTRACTThe primary experiment for HIFiRE-1 was to measure boundary-layer transition in hypersonic flight on a 7 degree halfangle, axisymmetric cone with a 2.5 mm radius bluntness. A secondary experiment measured mean and fluctuating pressure, and heat transfer on a cylinder-33-degreee-flare geometry. The ascent provided smooth-body, low angle-ofattack, boundary-layer transition at Mach numbers greater than 5. The end of turbulent-to-laminar transition occurred at Reynolds numbers between 10.3 to 12.2 million. Second-mode N-factors of approximately 14 correlated transition. A diamond-shaped trip retained turbulent flow until reaching a roughness Reynolds number Rekk = 2200. During re-entry, transition was measured around the circumference of the cone at Reynolds numbers ranging from 3 million on the leeside to 5 million on the windward side. In the shock-boundary layer interaction, maximum sound pressure levels of 173 dB were recorded upstream of the flare, and 185 dB on the flare itself. The principal goal of HIFiRE-5 was to measure hypersonic boundary layer transition on an elliptic cone. The second stage booster failed to ignite, so the experiment reached a maximum Mach number of only 3. Nevertheless, supersonic pressure and temperature data were obtained under laminar and turbulent flow, and flight systems were validated. Traveling and stationary crossflow instabilities were clearly measured for HIFiRE-5 in ground test in a quiet flow tunnel. The frequency, phase speed, and wave angle were all in good agreement with computations.

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Excitation of Crossflow Instabilities in a Swept Wing Boundary Layer

Cited by 24 publications

References 39 publications

Computational Analysis of the G-III Laminar Flow Glove

Computational Analysis of the G-III Laminar Flow Glove

On predicting receptivity to surface roughness in a compressible infinite swept wing boundary layer

HIFiRE-1 and HIFiRE-5 Test Results

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