Airfoil dynamic stall performance with large-amplitude motions

Francis, Michael S.; Keesee, J. E.

doi:10.2514/3.9146

Cited by 62 publications

(22 citation statements)

References 14 publications

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“…Calculations are now proceeding with linear pitch-up with a second (upper surface) separated wake. Experimental measurements of airfoils undergoing constant rate pitch-up motions have been taken at the Frank J. Seiler Research Laboratory (47). Three cases are considered briefly here for correlation purposes.…”

Section: Complete Procedur"mentioning

confidence: 99%

Prediction of Dynamic Stall Characteristics Using Advanced Non-Linear Panel Methods.

Maskew¹,

Dvorak²

1984

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Section: Complete Procedur"mentioning

confidence: 99%

Prediction of Dynamic Stall Characteristics Using Advanced Non-Linear Panel Methods.

Maskew¹,

Dvorak²

1984

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“…Lorber and Carta, 4 Albertson et al, 5 Walker et al, 6 among others have measured the surface pressure distributions. Francis and Keese 7 have found that the maximum lift coefficient increases monotonically until a nondimensional pitch rate of 0.025, it decreases thereafter. Jumper et al 8 concluded from their studies that the pivot point has a large effect on dynamic stall.…”

Section: Introductionmentioning

confidence: 99%

Schlieren studies of compressibility effects on dynamic stall of transiently pitching airfoils

Chandrasekhara

Ahmed²,

Carr

1993

Journal of Aircraft

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Compressibility effects on the flowfield of an airfoil executing rapid transient pitching motion from 0-60 deg over a wide range of Mach numbers and pitching rates were studied using a stroboscopic schlieren flow visualization technique. The studies have led to the first direct experimental documentation of multiple shocks on the airfoil upper surface flow for certain conditions. Also, at low Mach numbers, additional coherent vortical structures were found to be present along with the dynamic stall vortex, whereas at higher Mach numbers the flow was dominated by a single vortex. The delineating Mach number for significant compressibility effects was 0.3 and the dynamic stall process was accelerated by increasing the Mach number above that value. Increasing the pitch rate monotonically delayed stall to angles of attack as large as 27 deg.

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“…Various aspects of this problem are under investigation. The effect of pitch rate has been studied by Francis, Keese, and Retelle (1983) and by Walker, Helin, and Strickland (1985). Threedimensionaf effects have been documented· by Gad-el-Hak et al (1983), and Adler and Luttges (1985).…”

Section: Comentioning

confidence: 94%

Review of Unsteady, Driven, Separated Flows

Reynolds

Carr

1985

Shear Flow Control Conference

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This paper reviews the main features of separated flows that are driven by some sort of forced oscillation.Vorticity is the key to understanding such flows, and a review of the key concepts is included.Then each flow considered is discussed from the viewpoint of the vorticity framework.The flows include driven boundary layers, backstep separations, and dynamic stall on airfoils.Re Vorticity flux.Span-average pressure.R1~ynolds number.

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Airfoil dynamic stall performance with large-amplitude motions

Cited by 62 publications

References 14 publications

Prediction of Dynamic Stall Characteristics Using Advanced Non-Linear Panel Methods.

Prediction of Dynamic Stall Characteristics Using Advanced Non-Linear Panel Methods.

Schlieren studies of compressibility effects on dynamic stall of transiently pitching airfoils

Review of Unsteady, Driven, Separated Flows

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