In-Flight Receptivity Experiments on a 30-degree Swept-Wing Using Micron-sized Discrete Roughness Elements

Carpenter, Andrew L.

doi:10.2514/6.2009-590

Cited by 29 publications

(18 citation statements)

References 31 publications

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“…However, the necessary descent rate will vary based on model construction and local atmospheric conditions. Reference [10] contains addition information about the SWIFT model. nstructed from milled aluminum.…”

Section: Cooled Modelmentioning

confidence: 99%

Laminar-Turbulent Boundary Layer Transition Imaging Using IR Thermography

Crawford¹,

Duncan²,

West³

et al. 2013

OPJ

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Experimental techniques for imaging laminar-turbulent transition of boundary layers using IR thermography are presented for both flight and wind tunnel test environments. A brief overview of other transition detection techniques is discussed as motivation. A direct comparison is made between IR thermography and naphthalene flow visualization. A technique for obtaining quantitative transition location is presented.

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Section: Cooled Modelmentioning

confidence: 99%

Laminar-Turbulent Boundary Layer Transition Imaging Using IR Thermography

Crawford¹,

Duncan²,

West³

et al. 2013

OPJ

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“…Mode amplitudes are critical measurements that can reveal details of receptivity to surface roughness and validate stability predictions. Carpenter et al 1 developed an approach to calibrate hotfilms for varying shear stress and temperature by executing constant-altitude aircraft velocity sweeps before and after a dive to provide shear stress data at different temperature conditions.…”

Section: Introductionmentioning

confidence: 99%

Real-Time Measurement of Skin Friction Using Calibrated Multi-Element Hotfilm Arrays

Long

White

2012

28th Aerodynamic Measurement Technology, Ground Testing, and Flight Testing Conference

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This paper describes a general procedure for real-time calibrated measurement of skin friction using hotfilm sensors controlled by a constant voltage anemometer (CVA). Hotfilms are sensitive to air and substrate temperature and compensating for temperature dependence requires in situ estimates of heated and unheated hotfilm resistance. This can be done by rapidly alternating between overheat ratios. To verify the usefulness of this approach, a CVA was constructed to make in situ estimates of conductive dissipation into the substrate. Following previous work, the analysis approach assumes the air and substrate are in thermal equilibrium. Wind tunnel tests were conducted within a 3 × 4 foot wind tunnel at Texas A&M University. Hotfilms were installed along the chord of a NACA 0018 airfoil and calibrated to measure shear stress. The validity of the calibration approach using multiple overheats was tested for changing air and substrate temperature over 12 • C ranges. The calibration remains valid over temperature changes of this magnitude when the air and model remain in thermal equilibrium. However, when the air and substrate were not in thermal equilibrium over this temperature range the calibration failed. Future work must consider a more general formulation that accommodates unequal air and substrate temperatures and avoids electronic noise.

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“…This suppresses the growth of unstable crossflow waves that would otherwise cause transition [6,7]. DRE technology has already been demonstrated in the wind tunnel [6] and in flight [3,8] up to chord Reynolds numbers of 8 × 10 6 . The next major step is to show DRE effectiveness at increased Reynolds numbers.…”

Section: Introductionmentioning

confidence: 99%

Computational Evaluation and Linear Stability of a Transonic Laminar-Flow Wing Glove

Roberts

Reed

Saric

2015

Journal of Aircraft

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The Flight Research Laboratory at Texas A&M University has proposed conducting both natural laminar flow and passive laminar flow control flight-test experiments through NASA's Environmentally Responsible Aviation program in partnership with Dryden Flight Research Center and Langley Research Center. The flight-test program will further explore discrete roughness element technology and demonstrate its effectiveness at extending laminar flow beyond the natural transition location. Texas A&M University completed a wing-glove design, designated TAMU-06-05, that was to be installed on a Gulfstream III testbed aircraft. Detailed analysis on the wing-glove design effectiveness is given, focusing on flowfield behavior and boundary-layer stability characteristics near the glove using full-aircraft computational-fluid-dynamics calculations.= Mach number Re c = chord Reynolds number x∕c = chord length ratio

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In-Flight Receptivity Experiments on a 30-degree Swept-Wing Using Micron-sized Discrete Roughness Elements

Abstract: In-flight Receptivity Experiments on a 30-degree Swept-wing Using Micron-sized Discrete Roughness Elements.

Cited by 29 publications

References 31 publications

Laminar-Turbulent Boundary Layer Transition Imaging Using IR Thermography

Laminar-Turbulent Boundary Layer Transition Imaging Using IR Thermography

Real-Time Measurement of Skin Friction Using Calibrated Multi-Element Hotfilm Arrays

Computational Evaluation and Linear Stability of a Transonic Laminar-Flow Wing Glove

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