Measurements in a leading-edge separation bubble due to a simulated airfoil ice accretion

Bragg, Michael B.; Khodadoust, Abdollah; Spring, S. A.

doi:10.2514/3.11087

Cited by 62 publications

(39 citation statements)

References 10 publications

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“…angle-of-attack for two different Reynolds numbers. Both curves are indicative of a separation bubble flowfield aft of the large glaze ice shape (e.g., see Bragg, et al 22 ). The constant pressure region on the upper surface between x/c = -0.02 and 0.16 indicates flow separation from the ice shape.…”

Section: Iced Airfoil Resultsmentioning

confidence: 99%

A Wind Tunnel Study of Icing Effects on a Business Jet Airfoil

Addy

Broeren

Zoeckler

et al. 2003

41st Aerospace Sciences Meeting and Exhibit

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Section: Iced Airfoil Resultsmentioning

confidence: 99%

A Wind Tunnel Study of Icing Effects on a Business Jet Airfoil

Addy

Broeren

Zoeckler

et al. 2003

41st Aerospace Sciences Meeting and Exhibit

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“…Similar to separation bubble on a curved surface (Bragg et al 1992), pressure recovery becomes possible as the shear layer entrains high energy external flow and the bubble reattaches (Fig. 10).…”

Section: Resultsmentioning

confidence: 99%

“…The reattachment location occurred near the location where the clean and iced pressure distributions intersect on the upper and lower surface. This method of approximating the bubble reattachment location as the intersection of the clean and iced pressure distributions was investigated by Bragg et al(1992) and was found to be accurate enough. In present study, this method was employed for estimating reattachment point of separated shear layer, downstream of the horn.…”

Section: Resultsmentioning

confidence: 99%

Experimental Investigation on the Aerodynamic Performance of NLF-0414 Iced-Airfoil

Ebrahimi¹,

Hajipour²,

Hasheminasa³

2016

JAFM

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Icing phenomenon on a natural laminar flow airfoil (NLF-0414) has been experimentally investigated. Double horn glaze ice geometry which was acquired during a 15 minutes spray time at−2.23℃ with liquid water content and a median volumetric diameter of 1.0 g/m 3 and 20 μm, has been extracted from database of NASA Lewis Research Center. Pressure distribution over airfoil surfacewas evaluated at angles of attack between -2 to 6 degreesfor both iced and clean airfoils. Aerodynamics performance degradation of the iced airfoil has been studied and it is shown that double horn ice accretion, due to its unique geometry, severely affects aerodynamic characteristics of natural laminar flow airfoils. Reattachment locations have been evaluated for upper and lower separation bubbles. The upper surface separation bubble was seen to increase in size in contrary to the lower surface separation bubble.

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“…A more detailed discussion of the 2-D ice-induced separation bubbles can be found in ref. 13. As the flow moves downstream the shear layer thickens and the amount of reverse flow decreases until the boundary layer reattaches around x/c = 0.16.…”

Section: -D Resultsmentioning

confidence: 99%

Aerodynamics of a finite wing with simulated ice

Khodadoust

Bragg

1995

Journal of Aircraft

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The effect of a simulated glaze ice accretion on the aerodynamic performance of a three-dimensional wing is studied experimentally.Results are reviewed from earlier two-dimensional tests which show the character of the large leading-edge separation bubbles caused by the simulated ice accretion, .Thh e 2-D bubbles are found to closely resemble well known airfoil laminar separation bubbles.For the 3-D experiments a semispan wing of effective aspect ratio five was mounted from the sidewall of the UIUC subsonic wind tunnel.The model uses a NACA 0012 airfoil section on a rectangular planform with interchangeabl e tip and root sections to allow for 0-and 30-degree sweep. A three-component sidewall balance was used to measure lift, drag and pitching moment on the clean and iced model. Fluorescent oil flow visualization has been performed on the iced model and reveals extensive spanwise and vortical flow in the separation bubble aft of the upper surface horn. Sidewall interaction and spanwise nonuniformity are also seen on the unswept model. Comparisons to the computed flow fields are shown. Results are also shown for roughness effects on the straight wing. Sand grain roughness on the ice shape is seen to have a different effect than isolated 3-D roughness elements,

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Measurements in a leading-edge separation bubble due to a simulated airfoil ice accretion

Cited by 62 publications

References 10 publications

A Wind Tunnel Study of Icing Effects on a Business Jet Airfoil

A Wind Tunnel Study of Icing Effects on a Business Jet Airfoil

Experimental Investigation on the Aerodynamic Performance of NLF-0414 Iced-Airfoil

Aerodynamics of a finite wing with simulated ice

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